Power generating windbags and waterbags

ABSTRACT

A method of using a bagged power generation system comprising windbags and waterbags integrated with drones and adapting drone technologies for harnessing wind and water power to produce electricity. An extremely scalable and environmentally friendly method, system, apparatus, equipment, techniques and ecosystem configured to produce renewable green energy with high productivity and efficiency.

This application is a continuation-in-part of U.S. application Ser. No.15/270,500, filed Sep. 20, 2016, which is a continuation of U.S.application Ser. No. 14/976,855, filed Dec. 21, 2015, now U.S. Pat. No.9,447,775, which is a continuation of U.S. application Ser. No.14/608,511, filed Jan. 29, 2015, now U.S. Pat. No. 9,234,501, which is acontinuation of U.S. application Ser. No. 13/870,413, filed Apr. 25,2013, now U.S. Pat. No. 8,963,362, which in turn claims priority to SGapplication no. 201302987-1, filed Apr. 19, 2013 and SG application No.201203067-2, filed Apr. 26, 2012.

FIELD OF THE INVENTIONS

Present invention relates to the utility purpose of deploying drones andadapting drone technologies for harnessing high altitude wind energy anddeep sea ocean energy to generate renewable energy; displacing use offossil fuels; mitigating the deadly effects of catastrophic globalclimate change. To safeguard and preserve our one and onlylife-support-system—Earth's Biosphere; in a habitable condition for allhumans, animal and plant species to continue living. That the air webreathe, the water we drink remains clean and healthy; not poisoned bythe toxic wastes we generate. Deploying drones to serve humanity. Togenerate clean energy; to preserve clean air; clean water; and a healthyplanet Earth for future generations! That humans doesn't follow thedinosaurs—into extinction! Yeah, drones! Drones to the rescue ofhumanity! Drones to save mankind from this self-inflicted ecologicalsuicide!

The harnessing of renewable “green” energy from the mass movement ofnaturally occurring fluid elements comprising wind; the capture andtransformation of this kinetic energy into useful mechanical energy bymeans of specialized vehicles and a bagged power generation systemconfigured for producing electricity comprising: wind poweredgenerators. In particular wind energy comprising: high altitude windenergy; the Jet Stream. The harnessing and transformation of the fluid'skinetic energy into useful mechanical energy by means of tethersattached to the Hybrid Aerial Vehicles (HAV-400); production of storedpotential energy; and electricity by means of generators. Specializedairborne Flying Energy Generators (FEGs) comprising HAV-400 configuredto harness the kinetic energy of high altitude winds for doing usefulwork. A method, system, equipment, apparatus, techniques and a droneecosystem configured with vertical scalability and a quantum leap in thegeneration of renewable green energy: electricity, in comparison withexisting systems at a minimized environmental and aesthetic cost.

BACKGROUND OF THE INVENTIONS

Present methods of harnessing wind energy by means of: kites, windmills, wind turbines, kytoons, airfoils, etc.; use of sails on boat,ship or sledge for traction is known; as is the capture of water energyby means of: water mills, water wheels, turbines; balloons mounted onthe sea-bed, floatation based devices, etc.; in converting the kineticenergy of wind into mechanical energy to do useful work: mills to grindflour, pump water, etc. including aero-electric power and hydro-electricpower generation. However, some devices like: wind mills, wind turbinesmay be deficient and self-limiting due to (i) the minimized surface areafor capture of the kinetic energy of the fluid medium as evidenced bythe limited size and number of turbine blades, rotors, propellers,spokes; sails, etc. that may be affixed to an apparatus; (ii) theextremely short, momentary, contact time between the drive surface andthe moving fluid medium providing the kinetic energy lasting a fewseconds; and (iii) harnessing the kinetic energy in an ad-hoc randomizedmanner. Harnessing the energies of mother-nature in quantities hugeenough for global consumption by means of utility scale generationplants/or farms; may require different approaches and solutions fromconventional methods, systems and apparatus presently available. Inparticular high altitude wind energy, the Roaring 40's, the Furious50's, the Shrieking/or Screaming 60's, the Jet Stream (exceeds 92 km/h;up to 398 km/h).

The low altitude sector (800 m to 1 km) of wind energy typicallyharnessed by wind turbines mounted on fixed towers comprises about 2% ofthe total global wind power. Whereas 98% of the global wind energy liesout of reach at a height of above 800 meters; and may be extracted bymeans of airborne wind energy systems operating above this altitude.

Present invention discloses methods of using tethered, Hybrid AerialVehicles (HAV-400) which may be transformed from their original airplaneshaped bodies into different shapes as configured such as: puffed up andenlarged; Delta-shape; V-shape; etc. Thus maximizing its liftingefficiency; in effect being transformed into an airborne sky-crane; awind-driven-sky-lifting vehicle capable of harnessing kinetic energy 11of wind 10 movement; transforming it into green electricity directly; orindirectly when used in tandem with stored potential energy systems forgenerating potential energies which may in turn be converted intoelectricity later, as and when needed; such as 100% artificial greenhydro-electricity. HAV-400 may also be used as a prime-mover to liftarrays of wind turbines/or carrier-apparatus mounted with wind turbinesinto high altitude in order to harness much more powerful wind energy.Configured as a glider drone, the engine of HAV-400 wind crane may bepowered off at height; utilizing the surrounding wind power to generateaerodynamic lift; to power its internal system of ram air turbines (RAT)71 aa; 71 ab; 71 ac; for running onboard systems and equipment.

The forward moving force/or kinetic energy 11 of the wind 10 moving overthe aerodynamically shaped surfaces of the HAV-400 creates a hugeaerodynamic force lifting the vehicle vertically upwards at an angularinclination relative to the tether line 50 aa cum reel system 52 aa.This upward lifting force pulling on the attached tether line (kineticenergy 11) exerted a tensional force which turned the tether spool 52aa/or line reel drums 52 aa. This rotational movement (mechanical energy12) is transmitted via a transmission gear-box 53 ag; and used to powera driven appliance 54 ag comprising: a pump/or, compressor to producepotential energy 13/or, a generator to produce electrical energy 14. Amultitude of such HAVs-400 and tethers-lines 50 ag (drive unit 51 ag)comprising thousands/or hundreds of thousands in number may be timed andarranged to take turns to drive the generators 54 ag (driven unit 55 ag)to produce Gwh/year or Twh/year of electricity 14. The HAV-400 andattached tether-line 50 ag comprises drive unit 51 ag. The revolvingbobbin/or tether spool 52 ag/or line-reel-drum 52 ag; gear box 53 ag cumgenerator 54 ag comprises the driven unit 55 ag. A winding motor 49 agmay be used to operate the reel-drum 52 ag to retract back the tetherline 50 ag and HAV-400. Towards the end of the power run/or end-of-run(EOR) point 288 aa, the HAV-400 may be depowered by changing itsaerodynamic wings profile into neutral lift; and then into negativelift; retracted, retrieved and pulled back (free load) to start-of-run(SOR) point 16 aa; “ground zero”; where it may operably change itsaerodynamic body profile into positive lift; and redeployed.

SUMMARY

Present invention discloses a method, system, equipment, apparatus,techniques and drone ecosystem for generating electrical power,comprising of: a shape-morphing glider-drones HAV-400, a mobilenavigable vehicle body pulling a tether (drive unit 51 ag) attached toan electricity generation module (driven unit 55 ag). Such a dynamicmethod of power generation utilizes a vehicle generating a tremendousamount of aerodynamic lift; thus moving the vehicle vertically upwardsat an angle relative to the direction of flow of the fluid medium; withthe tensile force created in the tether line 50 ag powering thegeneration module to produce electricity for the duration of its entireupward movement. In the wind-borne form this apparatus may be configuredas a hybrid Unmanned Aerial Vehicle (UAV-400)/or Hybrid Aerial Vehicle(HAV-400). Equipment, apparatus and an ecosystem for operating theaerial drone may be mounted on and borne by the vehicle body, including:flight control surfaces, tether lines, bridle lines, control lines 46,retract lines, winches, motorized turbo-fans, propellers,side-thrusters, batteries, engines, compressed air-tanks, helium tanks,fuel tanks, balloons, ram-air-turbines, etc. Enabling capabilitiesincludes providing airborne work-stations 44 aa for station hopping,thus extending the range and power-run of the drive units 51. Theairborne platform may comprise of highly specialized supporting systemssuch as the Unmanned Aircraft System (UAS) infrastructure for aerialdrones. Said vehicles being remotely navigated, controlled and operatedby human navigators by means of transmission wire-lines embedded intothe tether lines 50 ag; or remotely by means of radio frequency (RF) andsonar signals.

Disclosed herein is a motion-centric method; and dynamic system ofgenerating power by means of specially configured motion basedvehicles/motile apparatus; navigable vehicles traversing a fluid mediumon a relatively linear trajectory or path of travel (from SOR point 16aa to EOR point 288 aa); said multitude of fluid propelled navigablevehicles travelling in proximity may be remotely manipulated to avoidcollision/or to maintain a journey free from interference from likevehicles. Said navigational means comprises ground based and onboardradar and sonar transmitters, receivers, sensors and cameras linked to acomputerized Advanced Warning System for proximity warning to preventcollision. Including propulsion engines 408; thrusters 70 ae; controlsurfaces comprising: wings 404; stabilizers 405; tail controls 406;emergency equipment comprising solid propellant discharge nozzles 242ar; compressed air nozzles 242 aa.

Computerized self-navigation capability enabled by means of dronetechnologies along an assigned trajectory may also be incorporated intothe guidance system of the drones. The main thrust of present inventioncomprises of: a HAV-400; essential components comprising a: shapemorphing vehicular body; tether; surface based energy generation system.A tether line for transmitting the motive forces/or kinetic energy ofthe fluid propelled vehicle to a ground and/or surface based electricitygeneration system. The motion-centric vehicle moving vertically at adiagonal angle; extracting their energies as they traveled from the SORpoint 16 aa to the EOR point 288 aa; generating power continuously andconsistently for the duration of the whole upward journey. The fullforce of the fluid's aerodynamic lift may be imparted onto thewidespread wings of the HAV-400. The desired amount of drag force may beset into the generator system—manually by hand; computerized autocontrols or varied accordingly to maintain optimal operating conditions.Shape morphing wings attached to the vehicle bodies may be deployed andretracted while traversing in said fluid medium as and when desired/orcommanded; as the vehicle navigated along a designated trajectory. Thevehicle body and wings profile may be altered, to shrink and extend inshape; size; surface area; to provide changes in its aerodynamicconfiguration. Such that the HAV-400 changes its lifting capabilitiescomprising: positive lift (vehicle moves upward); neutral lift (vehiclestays at stationary height); and negative lift (vehicle moves downward).

BRIEF DESCRIPTION OF THE DRAWINGS

Preferred embodiments of the present invention will now be describedwith reference to the accompanying drawings wherein:—

FIG. 1A shows details of a fully deployed HAV-400.

FIG. 1B shows details of the cross-sectional side view 1B-1B of FIG. 1A;FIG. 1C shows details of FIG. 1B with the drone's body at maximuminflation and generation of maximum aerodynamic lift.

FIG. 1D shows details of the composition, components and body structureof HAV-400.

FIG. 1E shows details of a compressed air generation and helium gasrecycling system.

FIG. 1F shows details of the frontal view (fore) of FIG. 1A; and theinternal construction and structural components of HAV-400's body atmaximum inflation or lift.

FIG. 1G shows details of FIG. 1F with HAV-400's body profile at neutrallift; while FIG. 1H shows details of the body profile at negative lift.

FIG. 1I shows details of the original body of HAV-400M. FIG. 1J showsdetails of a fully morphed variant HAV-400M with extended wind engagingbag.

FIG. 1K shows details of a plan view of the shifting body contours ofHAV-400.

FIG. 1L shows details of the deployment of wind engaging bag extended atthe periphery of HAV-400.

FIG. 1M shows details of a plurality of UATV-80 aa flexibly attached toHAV-400.

FIG. 1N shows details of an air-rib 277 aa and solid rib-cage structure.

FIG. 1O shows details of attachment between plates 416 and metal ribs.

FIG. 2A and FIG. 2B shows details of the use of a HAV-400 in supportingrole.

FIG. 2C shows details of a plurality of HAV-400 lifting an aerial workstation enabling servicing and tether lines swapping of HAV-100 aa.

FIG. 2D to FIG. 2E shows details of an airborne docking sub-system 430.

FIG. 2F to FIG. 2H shows details of the sequential deployment phases ofa HAV-100 aa upon release from docking sub-system 430 of work station 44ab.

FIG. 2I shows details of the forces generated on a tethered HAV-400.

FIG. 3A to FIG. 3B shows details of sub-system 440 and sequential phasesand locations of a HAV-400 used with driven unit 55 ag to produceelectricity.

FIG. 3C shows details of sub-system 450 comprising a stored potentialenergy system for producing electricity on demand. FIG. 3D shows detailsof sub-system 460 comprising of a pumped hydro-electricity generationsystem.

FIG. 4A shows details of a sub-system 470 comprising a line of windturbines airlifted by HAV-400. FIG. 4B shows details of sub-system 480comprising an array of wind turbines built into a framework, carriedaloft.

FIG. 4C shows details of the sectional side view of a counter rotatingdouble sided turbine generator. FIG. 4D shows a sectional view 4D-4D ofthe generator.

FIG. 4E shows details of the side view; while FIG. 4F shows thesectional plan view 4F-4F of a vertically oriented counter rotatingdouble sided turbine discs generator.

FIG. 4G shows details of a quad-bladed turbine generator of FIG. 4C; theturbine blades embedded with generating elements.

FIG. 4H shows details of a counter-rotating double sided wind turbinegenerator; the turbine blades embedded with generating elements.

FIG. 4I shows details of a counter-rotating vertical shaft wind turbinegenerator.

FIG. 5A shows details of a plan view; while FIG. 5B shows the sectionalside view 5B-5B of a multi-tiered counter-rotating turbine generator.

FIG. 5C shows details of an airborne turbine generator lifted verticallyby a HAV-400; while FIG. 5D shows a turbine generator lifted in aninclined position.

FIG. 5E shows details of the front view of a three bladed wind turbinegenerator; while FIG. 5F shows the front view of a six bladed turbinegenerator. FIG. 5G shows the front view of a multi-bladed turbinegenerator.

FIG. 5H shows details of the sectional side view 5H-5H of FIG. 5G; whileFIG. 5I shows the sectional side view 5I-5I of a double layeredarrangement (side by side; or over-under configuration) of the twinturbine generator of FIG. 5E; FIG. 5F and FIG. 5H.

FIG. 5J shows details of the sectional side view of a double layeredarrangement (side by side; or over-under configuration) of the twinturbine generator of FIG. 5A and FIG. 5B.

FIG. 5K shows details of a HAV-400 wind-lifter carrying aloft aplurality of wind turbines 471; 500; 500 a. FIG. 5L shows a rackcontainer for keeping wind turbines.

FIG. 5M shows details of a HAV-400 wind-lifter carrying aloft anairborne wind turbine 500 a in an inclined position. Including aseaborne ecosystem for processing the renewable energies harvested bymeans of floating electrolyzer plants.

FIG. 6A shows details of an airborne wind energy harvesting system 510 aby means of windbags. FIG. 6B and FIG. 6C shows more detailedillustration of the main components. FIG. 6D and FIG. 6E shows the finedetails of FIG. 6B and FIG. 6C. FIG. 6F shows an optional arrangementfor avoiding line interference. FIG. 6G shows a high altitude groundstation used with an airborne station.

FIG. 6H shows details of a locking clamp mechanism for securing guidelines. FIG. 6I shows details of the side view; while FIG. 6J shows thefront view of robotic limbs holding guide lines securely.

FIG. 6K shows details of a windbag outfitted with accessories. FIG. 6Lshows a RF activated pressure control apparatus; and air nozzle. FIG. 6Mshows a telescopic cover and string 33 aa. FIG. 6N shows details of therotational sequence in which a plurality of generators 55 aa may bepositioned relative to the power run phase; retract phase; standbyphase.

FIG. 6O shows details of a seaborne water energy harvesting system 510 uenabled by means of water-bags.

FIG. 6P shows details of an improved system 76 av in power runcomprising multiple windbags for harvesting wind and/or water energy;guided by a navigation unit HAV-400. A water-bags system 222 av forharvesting water energy. FIG. 6Q shows the retraction phase of thesystem.

FIG. 6R shows details of adaptation of underwater seamounts 555 foranchoring cables for surface vessels harnessing and processing renewableenergies. FIG. 6S shows details of securing an anchoring beam; and aplug in caverns.

FIG. 6T to FIG. 6W shows details of a funnel shaped undersea structureto converge sea water to power water turbines. FIG. 6X shows details ofa turbines tunnel.

FIG. 6Y shows details of a plurality of submerged water turbines.

FIG. 7A shows details of a plurality of glider drones HAV-400 toincrease tensile force acting on a driven unit.

FIG. 7B shows details of system 600; in which the tensile force from aplurality of drive units may be transmitted back to a centralized powergeneration plant.

FIG. 7C shows details of line reel drum 582 integrated with the gearbox583; clutch 587; and retract motor 589.

FIG. 7D shows details of system 600; with a plurality of discsgenerators 590 d. FIG. 7E shows details of said dual discs generator.FIG. 7F shows details of two inter-connected line reel drums.

FIG. 7G shows details of system 600; with new extension apparatus totransmit the harnessed energies to the generator 590 h. FIG. 7H showsdetails of counter rotating generator 590 h.

FIG. 7I shows details of improving the efficiency of a combined cyclegenerator.

FIG. 8A shows details of using water-bags to divert and converge oceancurrent into a seaborne hydro power generation tunnel. FIG. 8B showsdetails of a parallel windbags system to concentrate wind current intoan aero power generation system.

FIG. 8C shows details of a flying carpet system comprising strips ofsolar fabrics mounted on light weight aero-foams; carried by gliderdrones HAV-400. FIG. 8D shows the use of such apparatus on water surfaceas solar energy collectors.

DETAILED DESCRIPTION OF THE INVENTIONS

The structural configuration, concept, method and system of providing anunmanned morphing HAV-400 for harnessing and extracting the energiescontained in a moving air current (wind) for the generation ofelectricity; is herein disclosed. Transforming its kinetic energy intomechanical and then electrical energy by means of a tether.

The working principal of a HAV-400 lies in maximizing generation ofaerodynamic lift. The airborne system may comprise of: customized aerialdrone HAV-400 and tether 50 ag (Drive Unit 51 ag); Generation Moduleshousing the tethers-line reels 52 ag, gear-box 53 ag, generators 54 ag(Driven Unit 55 ag); computerized ground control systems, control links;navigators; supporting systems, equipment; radar system, GPS; InertialNavigation System; parking aprons, control and command centre; UnmannedAerial Tow Vehicles (UATV) 80 aa; power collection grid; etc. DrivenUnit 55 aa may be integrated with other mechanical components such asair compressors; water pumps. The drive unit may be used to lift orcarry heavy loads such as containers filled with fluid (water); solidblocks of concrete; metal; rocks; earth; timber; etc.

Glider drones HAV-400 may be used to lift a variety of items into highaltitude to harvest wind energy such as: wind turbines 490 h; 490 d; 477v 500 a; 500 b; 500 c; 500 d; airborne work stations; air-bridges 429 p;429 r; control a multitude of drive units 30 aa to generate power; drivegenerators 584; 590 d; 590 h; etc. The combination of: a distributedsystem for extraction of energies comprising: high altitude wind currentand deep sea ocean current; a tensile force transmission system to; autility scale centralized power generation plant 585. Airborne windenergy harvesting system 510 a using windbags; seaborne energyharvesting system 510 u using water-bags.

FIG. 1A illustrates a deployed glider-drone HAV-400 with its body partsfully extended to generate aerodynamic lift; connected to a load, drivenunit 55 ag by means of tether 50 ag; while FIG. 1B illustrates thecross-sectional length-wise side view 1B-1B of FIG. 1A with an inflatedbody profile. FIG. 1C illustrates further enlargement and puffing-up ofthe body of FIG. 1B to attain maximum inflation, for generating themaximum lift configuration that the drone had been designed to produce.Also illustrated are: wind inlet port 401; hollow cavity 402; exit port403; control surfaces comprising: wings 404 a, 404 b; stabilizers 405 a,405 b, 405 c, 405 d, 405 e; tail controls 406 a, 406 b, 406 c; wheels407 a, 407 b, 407 c; engine 408; cooling fins 418 a. Since the HAV-400operates as a tethered glider-drone 99% of the time; engine 408 may notbe required at height. It may be used during take-off and for emergencypropulsion purposes only.

Airplane shaped, HAV-400 may comprise of a flying-wings body designwherein, the whole body of the vehicle may take the form of, and beshaped like the profile of an aircraft's wings; configured with standardconventional flight control surfaces comprising wings 404; sidestabilizers 405; main vertical stabilizer 406 a; horizontal stabilizers406 b; 406 c; rudder; slats; flaps; ailerons; elevators. Alike typicalwings of an airplane; ailerons and flaps present in wings 404; may bemanipulated to minimize or maximize aerodynamic lift generation, flightcontrol and loading capacity of the drone. HAV-400 looks much like theshape of a manta-ray, but with the capability of a puffer fish to cansuck in air, puffing up its stomach, distending its flat, thindiscus-like body into an enlarged balloon several times its originalbody size. In HAV-400 this feature is applied selectively to inflate anddeflate specific part(s) of the drone's body as and when required; tomanipulate generation of aerodynamic lift to ascend, stay aloft,descend. The motivation for adapting the flying-wings body configurationis for the purpose of: maximizing generation of aerodynamic lift fromthe harnessing of high altitude wind energy; and employing the morphingbody profile to do useful work for mankind. Not for the purpose of highspeed flight, fuel efficiency, cost savings, or stealth capability.

While tether line 50 ag bore the main load for doing useful work;HAV-400 may also be anchored and manipulated by means of control line 46aa or retract line 33 aa. At the drive end, tether 50 ag may beconnected to the three bridle lines 21 aa, 21 ab, 21 ac joined togetherat point 410. The three bridle lines may in turn be flexibly connectedto HAV-400 at points 409 a, 409 b, 409 c; on the drone's body, linked toconcealed winches 59 aa, 59 ab, 59 ac; sliding in and out via points409; during adjustment of lines and angular inclination of the drone'sbody relative to wind flow. At the driven end tether 50 ag may beconnected to the load, driven unit 55 ag for producing electricity.Flight control surfaces 404, 405, 406 may be manipulated and used tovary HAV-400's load carrying capacities; maximum lift (ascend), neutrallift (stay in position, hover) negative lift (descend). The leadingedge's angle of attack (of the drone's body) may be adjustedautomatically by varying the length of the 3 bridle lines 21 aa; 21 ab;21 ac; by means of concealed winches 59 aa; 59 ab; 59 ac; in tandem withvariability in the generation of aerodynamic lift produced by thevariable shape and form of the drone's body.

The HAVs-400 may be configured with one bridle line 21 aa attached tothe bow section (fore) at point 409 a; line 21 ab to starboard side atpoint 409 b; and line 21 ac to port side at point 409 c; joiningtogether with tether line 50 aa at point 410. The lengths of the bridlelines 21 may be adjusted by winches 59 aa; 59 ab; 59 ac; to tilt andvary the vehicle body's position and angular inclination relative to thewind direction; thus optimizing the HAV-400 body's angle of attack. Thisprovide a secondary means of adjustment; maximizing; or minimizing theHAV-400's aerodynamic load lifting capacities; apart from the primarygeneration of aerodynamic lift by means of the morphing body and changesin the wing's angle of attack.

Thus the directional, flight controls and load-lifting adjustments ofHAVs-400 may be effected by means of: (a) Variations in vehicle shape(morphing) by means of pneumatic system for inflating/or deflatingwindbags 420 system constituting the airframe; said windbags 420comprising: air-pillars 420 a; air-pouches 420 b; air-pads 420 c;air-packets 420 d; air-cells 420 e; air-ribs 277 aa, 277 ab. (b)Variations in the angles and length of the three bridle lines by meansof winches 59 aa; changing the position of the drone's body; and thusthe main body's leading edge's angle of attack. (c) Variations ofconventional wings and tail mounted flight control surfaces 404, 405,406. Sensors 411 on the drone's body interacts instantly with onboardand ground computer systems regarding its vital operating parameters andambient conditions; adjusting and correcting its flight parametersaccordingly.

FIG. 1D illustrates the preferred components used in constructingHAV-400. Solid structural framework 412 may comprise of: round pipes 412a; rectangular pipes 412 b; square pipes 412 c; girders; C-channels;V-channels; etc. Materials making up this body framework structure maycomprise of: metallic; composites; carbon-nano-fibers; fiber glass;ceramics; Kevlar; carbon fiber reinforced plastics; glass fiberreinforced plastics; quartz fiber reinforced plastics; aluminum glassfiber laminates; glass laminate aluminum reinforced epoxy (GLARE). Thisstructural framework is overlaid by the air-frame comprising layers offlaccid shaped air-bags 420 comprising air-pouches 420 b; air-pads 420c; air-hoses 413 a, air-tubes 413 b; covered by an external layer ofskin 415 bound by straps 415 a made of lifting harness materials;Dyneema; Spectra; Kevlar; etc. Solar fabrics 415 b may be embedded intothe fabric materials of the uppermost layer of skin 415 to harness solarenergy in flight. Optionally the skin 415 may be coated with a layer ofreflective material to reflect back the sun's rays outward into space;creating an albedo effect. Deployed in large numbers, HAVs-400 may alsoprovide a form of sun-shade to the surface below; reducing ambienttemperature and the intensity of heat waves. This may be similar ineffect to proposed geo-engineering initiatives of spraying a layer ofairborne chemicals/surfactants on the ocean's surface to reflectsunlight back into space to mitigate the severity of global warming cumglobal climate change.

Optionally, the external surface of the vehicle body may comprise oflarge pieces of over-lapping scale-like-plates 416; an exo-skeletonproviding strength and support. Such external plates may beinter-connected by a layer of pliable, durable membrane like material;and in turn mounted on an inner layer of fabric skin; replicating thereptilian skin in design; or flexibly connected to a framework andnetwork structure of pliable ribs 446 by mean of sliding rings 447(Refer FIG. 1O). The plates may be made of: metals; ceramics;composites; carbon fibers; plastics; thermoplastics, reinforced fabrics,etc. While the internals of the body comprising of: windbags, airbags,air-ribs, fabric; etc. may be arranged wherein a plurality of layersconfigured on top of one another may be inflated or deflatedindividually or in groups upon requirement. Such that variations inheight or thickness of the body as desired, may be achieved by means ofinflating and deflating designated pieces or groups of airbags 420; orlayers of such airbags 420 stacked on top of each other. Minuteadjustments to the airframe may be made by means of small sizedair-packets 420 d; air-cells 420 e. While adjustment of air pressure maybe used to balance the turgidity between air-ribs 277 aa and 277 ab inorder to optimize external shape and aerodynamic lift generation ofHAV-400. (Refer FIG. 1K)

The structural configuration of HAV-400 may comprise of two maincomponents: (1) a solid skeletal body framework 412; covered by anexternal (2) airframe consisting of airbags 420 system which may beselectively inflated or deflated by means of pneumatic control anddistribution system 421; with commands from computerized algorithms,logic and programs. The structural configuration of windbags/or airbagssystem 420 comprises a plurality of variably shaped: air-pillars 420 a;air-pouches 420 b; air-pads 420 c; air-packets 420 d; air-cells 420 e;air-ribs 277 aa, 277 ab; including: air-hoses 413 a, air-tubes 413 b;2-ways switching valves 414, 3-ways switching valves 414. The termairframe in present invention differs slightly from the normal meaningof “airframe” used to describe aircrafts; as it comprises 100% airinflated windbags 420 filled with compressed air/or helium gas;providing turgidity to the drone's body; giving HAV-400 its externalshape, contour, morphology. Such that inflation and deflation ofstrategically positioned air-bags 420 changes the shape of the drone'sbody enhancing its aerodynamic properties; enabling it to attainneutral, power-up, depowering capabilities; allowing useful work to bedone safely. Solid skeletal body framework 412 may comprise about 20% ofthe total drone body's component.

A ram-air-turbine (RAT) 71 is central to the working mechanisms ofHAV-400; as a huge amount of compressed air is required for inflatingthe airframe of the vehicle comprising air-bags system 420 consisting ofa variety of shaped: air-pillars 420 a; air-pouches 420 b; air-pads 420c; air-packets 420 d; air-cells 420 e; air-ribs 277 aa, 277 ab;including: air-hoses 413 a, air-tubes 413 b; switching valves 414 a and414 b activated by means of computerized signals. Three ram-air-turbines(RAT) 71 aa, 71 ab, 71 ac may be configured in series into the center ofthe drone's body for redundancy. An oval shaped hollow cavity 402 ranthe whole length of the drone's body, from the fore (bow) through theaft (stern). High speed wind enters via fore mounted wind-intake port401 driving ram-air-turbines RAT-71 aa; 71 ab; 71 ac mounted insidecavity 402; expended air exiting via aft mounted port 403. RAT-71 aa; 71ab may be used to produce compressed air; while 71 ac may be used togenerate electricity for onboard use. Compressed air produced by RAT-71aa driven compressor 417 may be cooled by means of air cooler 418;stored in cylinders 419; used to inflate the air-frame components as andwhen needed; and released into the atmosphere upon deflation of theair-bags 420. Optionally, HAV-400 may use lighter-than-air helium gas toinflate its air-frame.

Present invention discloses the use of high altitude wind current to:(1) Generate an aerodynamically shaped body profile (HAV-400) by meansof compressed air for inflating a multitude of windbags/or airbags 420.(2) Creating aerodynamic lift on said body (HAV-400) of (1) above; to douseful and productive work for mankind; in a self-sustaining airbornesystem without the need for external input of energy; except for theinitial lift to become airborne. Minor repairs might be carried out onthe flying airborne platform 44 ab; which double as a refueling stationstore, parking lot, crew change, etc. The drone is configured to stayairborne for extended periods of time until major maintenance requiredfor it to land.

FIG. 1E illustrates a compressed air generation sub-system 422 a and/ora helium gas recycle sub-system 422 b. In sub-system 422 a, compressedair generated by means of RAT-71 aa; 71 ab driven compressor 417 may becooled down by an air-fin cooler 418; stored in cylinders 419;controllably released by means of a computerized pneumatic control anddistribution system 421; to selectively inflate the air-frame comprisingspecific airbags 420; by means of a network of air-hoses 413 a,air-tubes 413 b, two-ways switching valves 414 a and three-waysswitching valves 414 b activated by means of computerized signals fromsystem 421. Valves 414 may be operated to inflate airbags 420 withcompressed air from tank 419; and to deflate airbags 420 by venting offinto the atmosphere; in a controlled manner as and when required.Cooling fins 418 a of the air-fin cooler 418 may be embedded into thesides of hollow cavity 402. Optionally, if helium gas is used forinflating airbags 420, the helium gas recycle sub-system 422 b may beadapted. Due to its rarity, helium gas is not vented off after use, butrecycled back to RAT-71 aa driven compressor 417; air-fin cooler 418;containers 419 and reused repeatedly. Air-Driven-Generators (ADG);Air-Driven-Compressors (ADC) comprising Ram-Air-Turbines (RATs) 71 aa;71 ab; 71 ac may be used to power all systems abroad HAV-400: hydraulic,electrical, pneumatic systems; for operating flight control surfaces;pressurization of the airbags 420 system; directional control air jets242 aa; engines 70 aa, winches 59 aa, etc. All components and materialsused being designed and selected for their superior propertiescomprising: lightweight; durability; pliability; reliability; superbintegrity; fire-resistance; etc.

FIG. 1F illustrates the cross-sectional breath-wise front view (bow) ofthe HAV-400 of FIG. 1A; and structural components of HAV-400's body atmaximum inflation and lift (refer FIG. 1C). A large oval shaped windinlet port 401 is located at the center-bow of the drone's body; lyingatop solid structural components 412; covered by the external airframestructure 420; including: wings 404; main vertical rudder 406 a; topsidestabilizers 405 a, 405 b; hull side stabilizers 405 c, 405 d, 405 e;integrated with wheels 407 a, 407 b, 407 c. Also shown are internalconstruction and components of HAV-400; structural arrangement andarchitectural configuration of the vehicle's airframe mechanismcomprising airbags system 420. The variety of shaped inflatable fabricairbags 420 system comprising: air-pillars 420 a; air-pouches 420 b;air-pads 420 c; air-packets 420 d; air-cells 420 e; air-ribs 277 aa, 277ab. Air-ribs 277 aa may be configured around the circumference of theelliptically shaped HAV-400; while air-ribs 277 ab may be configured tosupport top deck 423 d and underbelly 423 u surfaces. Air-pillars 420 aare the equivalent of structural beams providing support for the topdeck 423 d and underbelly surfaces 423 u of the drone's body; etc.giving it external shape and form. Thus air-pillars 420 a may comprisethicker and much more robust fabrics to withstand much higher pressurerequired than the air-pouches 420 b; air-pads 420 c; air-packets 420 d;air-cells 420 e; which are the equivalent of body tissues. Air-pouches420 b comprises large box like cubes in form; while air-pads 420 ccomprises square or rectangular pieces of flat mattress/or cushionshaped. Air-packets 420 d forms small adjustment pockets of air; whileair-cells 420 e enables minute space filling of gaps and topping up inbetween the other larger shaped bodies of airbags for a smooth exteriorbody surface. This is important in establishing a smooth air flow foroptimized creation of aerodynamic lift. The airframe provided bycompressed air or helium gas in airbags 420 works in tandem withsolid-frame components 412 (refer FIG. 1D) which provides the structuralskeletal backbones of the HAV-400.

Internal airbags configured into the top deck 423 d and underbelly 423 uportions of the body may be selectively inflated; or, deflated; theiractivation varied to change the body shape of the HAV-400; and theiraerodynamic lifting capacities as and when required, in tandem withvariations in the “angle of attack” of the body's leading edge and thewing's 404 leading edge. Wherein, neutral aerodynamic lift of a vehiclemay be used to support the HAV-400's own weight of (e.g. 1 to 10 tons),keeping it airborne in a relatively steady hovering location/position.While generation of positive aerodynamic lift up to maximum lift by thewings and morphed body of the HAV-400 may be used for its ascent;enabling lifting of its designed load from its standard hovering height(e.g. 1 km level) to a greater height (e.g. 10 km level). The requiredlift may be varied by adjusting the shape of the body and wings profileto suit the load (drag) it is required to lift up and carry.

At high altitude, high speed wind current (e.g. 100 km/h) might be ableto create adequate aerodynamic lift to power a tethered drone-gliderHAV-400 to lift a heavy load. Such that for a drone with an aerodynamiclift generating surface area comparable in dimension to that of acommercial aircraft (e.g. Boeing, Airbus); a “loaded-positiveaerodynamic lift” (e.g. 100 tons) may be achieved by means of balancingthe HAV-400's own weight (e.g. 20 ton) plus the added load it isbearing/useful work done (e.g. 80 tons); relative to the required liftcoefficient needed to keep the vehicle in a steady location/position.Negative aerodynamic lift (below neutral) generated by the morphing bodyand wings may be used for rapid descent of HAV-400; enabling retractionof tether lines 50 aa and for the HAV-400 to return from its EOR point(288 aa) to its SOR point (16 aa) speedily.

A flying-wings-work-horse, HAV-400 may be used for generation ofrenewable energies and performing a variety of other heavy liftingtasks. HAV-400 may be used: (a) In a supporting role; in enhancingefficiency of HAV-100 s; as a support vehicle (refer FIG. 2A to FIG. 2C)for provision of heavy lifting; enabling work stations 44 ab to stayairborne; (b) Independently by itself as drive unit 51 aa for generationof electricity; and stored potential energy. Three basic types oftraction lifts may be performed by HAV-400 comprising: (1) batch liftingof static load comprising a heavy body e.g. blocks of stone; timberlogs; etc. from one point to another point; (2) fixed position staticlift e.g. carrying aloft an array of wind turbines to harness highaltitude wind energy, and staying at a fixed location for an extendedperiod of time; (3) running lift; in which a continuous force is exertedthroughout its journey from SOR point 16 aa to EOR point 288 aa, e.g.running generators; pumps; compressors. HAV-400 may be configured withfixed bodily structure and deployed as such. Optionally, theairplane-shaped-body may be transformed into a variety of configurationscomprising: V-shape; Delta-shape; 5-angled; rectangular; /or, resemblinga full-moon-shaped-kite called the “wau-bulan”; etc.

FIG. 1G illustrates the front view and body profile of HAV-400 in ahovering position, in which the top deck 423 d curvature of the airframeis minimized (while underbelly 423 u remains the same) in comparisonwith FIG. 1F. The drone is at neutral aerodynamic lift; such thatminimum lift generated roughly equals the body weight/or mass of thedrone itself (zero load). While FIG. 1H illustrates generation ofnegative aerodynamic lift wherein the underbelly 423 u curvature of theairframe is increased (while top deck 423 d remains the same) incomparison with FIG. 1F; such that the drone descends from heightrapidly towards ground level.

FIG. 1I and FIG. 1J illustrates a variant form comprising a morphingkite-drone HAV-400M; configured with concealed extensions ofbody-framework comprising: wing frames 424, bow frame 425; body length426; and a collapsible arrangement of stowed windbag fabrics 30 aa;air-ribs 277 aa, 277 ab; etc. These concealed extendable and retractablesolid body frames 424; 425; 426; air-ribs 277 aa; and a plurality ofvariously shaped airbags 420 hidden within may be deployed therebytransforming, morphing the HAV-400M into an enlarged and elongatedbody-frame with increased length and breath. Whereas from wing-tip towing-tip; from nose to tail; the HAV-400M may be configured to vary from10 m (normal pre-launch; launching) morphing up to 20 m (after launch;airborne) upon full extension of the HAV-400M's concealed body parts 424c; 425 c; 426 c. Deployment of concealed fabric materials 30 aa storedlengthwise inside the belly of the main body transforms the drone into akite shaped wing-suit apparatus/or a kite; kite-drone;kite-glider-drone. Winches 59 aa and embedded lines 23 aa; 66 aa andpulley wheels 68 aa beneath the wing-span pulls the fabric material 30aa breath-wise, opening up the wing-suit. Inflated air-ribs 277 aa onthe periphery of fabric materials 30 aa kept the desired shape in place.Additional bridle lines 21 aa may be used to link fabrics 30 aa to thecommon joint 410. The fabric materials 30 aa may be deployed andretracted as required to harness high altitude wind energy. Solarfabrics 415 b may be embedded into bag fabrics 30 aa.

FIG. 1K illustrates the change in the circumference of the body shape ofHAV-400 between generation of maximum and minimum aerodynamic lift.Outer contour line 427 d indicates the extended circumference of thedrone's body when it is deflated and flaccid as shown in FIG. 1G; suchthat peripheral located air-ribs 277 aa are fully inflated and extendedwhile top deck located air-ribs 277 ab are deflated and flaccid; givingneutral/or minimum lift. Inner contour line 427 i indicates the shrunkencircumference of the drone's body when it is fully inflated and puffedup as shown in FIG. 1C; such that top deck air-ribs 277 ab are fullyinflated and extended while peripheral air-ribs 277 aa are deflated andflaccid; creating maximum lift; using minimum body mass.

FIG. 1L illustrates a variant form wherein HAV-400 may incorporatefabric materials 30 aa around the circumference of its body to engageand capture wind. The fabrics 30 aa may be extended and retracted asrequired by means of air-ribs 277 aa; embedded lines 23 aa; 66 aa; rings68 aa; pulley wheels 48 aa. Additional bridal lines 21 aa operated bywinch 59 aa may be used to secure the fabrics to joint 410. EnablingHAV-400 to be flown like a drone glider, kite-drone or windbag 30 aa.

FIG. 1M illustrates use of a plurality of unmanned aerial tow vehicles,UATV-80 aa; 80 ab; 80 ac; in providing propulsion for elevating aHAV-400 from ground to a suitable altitude for it to generate its ownlift before the towing vehicles detaches to return to ground. The threetowing vehicles may be flexibly attached to both the port and starboardwing-tips 404 and the main vertical stabilizer 406 a. Optionally, it maybe elevated and lifted up by means of another unit of HAV-400 alreadydeployed in high altitude; establish its own aerodynamic lift beforebeing uncoupled/released from the tether line 50 ab of the lifting unit.It may also be elevated by means of “airborne crane” comprising heavylift helicopters; or towed by a manned aircraft just like a glider tillit reaches a suitable altitude to generate its own lift before beingreleased.

FIG. 1N illustrates the use of air-ribs 277 aa concealed beneath theexoskeletal plates 416; in parts of the body and wings structure whichmay be configured to be pliable and bendable. Inflation or deflation ofthe air-ribs 277 aa causes the solid rib-cage 445 a; 445 b structure toextend or retract; pushing up or shrinking the exoskeletal plates 416covering the wings surface; and may be used to change the cross-sectionor profile of the wings structure. Such apparatus may be used on theleading edge portion of the wings; or the front leading edge of the mainbody, from the wind-intake port 401 (bow) running along both sides tillthe starboard and port side wings 404.

FIG. 1O illustrates a means of attachment in which the scale like plates416 of the exoskeleton may be flexibly connected to a framework andnetwork structure of solid ribs 446 by mean of a plurality of slidingrings 447.

FIG. 2A illustrates the use of HAV-400 in support of the deployment ofHAV-100 aa. The tether line 50 a′ of HAV-100 aa may be airlifted to ahigh elevation by means of a roller wheel 48 aa affixed to tether line50 aa borne by HAV-400. This allows HAV-100 aa to attain higheraltitudes speedily to harness more powerful winds to power driven unit55 ag. Thus HAV-400 displaces the use of tower 286 aa in FIG. 13C ofU.S. Pat. No. 8,963,362; U.S. Pat. No. 9,234,501.

FIG. 2B illustrates the optional use of HAV-400 in support of thedeployment of a master HAV-400′ leading a multitude of slave windbags 30aa. Master HAV-400′ displaces power consuming UAV-80 in FIG. 5A of U.S.Pat. No. 8,963,362; U.S. Pat. No. 9,234,501. Such a tandem flight ofHAV-400 and HAV-400′ requires zero input of external energy and has zeroemission as compared to using UAV-80 as previously disclosed. Otherprior art disclosures such as connecting windbag 30 aa to retract line33 at point 32 may also be used. Control line 46 aa or retract line 33aa may be used to retract back the whole drive unit 51 comprisingHAV-400′ and tether line 50 a″.

FIG. 2C illustrates the airborne version of station-hopping by means ofairborne work-station 44 ab; enabling the HAV-100 aa to fly from onestation to another without returning to base (please refer waterborneversion of station-hopping: FIG. 2A; FIG. 13D of U.S. Pat. No.8,963,362; U.S. Pat. No. 9,234,501). Wherein HAV-400 substitutes anddisplaces the use of HAV-45 in system 44. As such HAV-400 enabled system44 ab may also be used to support operation of flying airbags 30 aa andHAV-100 aa to generate renewable energy. A plurality of HAV-400 s may beused in lifting a work-station 44 ab (herein also referred to as StationB) into high altitude by means of tether 50 aa′; and staying there foran extended period of time. The system 44 ab may be configured tosupport a plurality of docking bays 428 w, 428 x, 428 y, 428 z, underair-bridge 429. Optionally, a docking bay 428 may be borne by tether 50aa′ from a single unit of HAV-400.

A unit of HAV-100 aa is shown attached to a docking bay 428 w mountedbeneath air-bridge 429 of Station B, 44 ab; and another unit HAV-100 abanchored to two docking bays 428 x; 428 y. Air-bridge 429 may beconstructed of rigid, solid structures comprising reinforced fiberglass;glass-reinforced plastics, carbon-fibers; composites; etc. The depleted(in run length) tether 50 aa attached to HAV-100 aa (originating fromupwind Station A, 44 aa) may be changed over to a fresh (full length)tether 50 ab (originating from Station B, 44 ab) enabling continuedoperation of HAV-100 aa to Station C, 44 ac; without being retractedback to Station A, 44 aa. Airborne checking, servicing, refueling andminor maintenance may also be carried out prior to taking off forStation C. Fresh tethers 50 ab attached to ground based driven units 55ab may be hoisted from grade up to Station B while depleted tethers 50aa may be lowered to ground level; and retracted to Station A by meansof a dedicated HAV-400; or ground based facilities. Such capabilitiesenhances flexibility, efficiency and productivity of the renewable powergeneration plant.

FIG. 2D to FIG. 2E illustrates an anchoring sub-system 430 enabling thelink-up, hook-up and docking of a depowered HAV-100 aa to a docking bay428 w mounted beneath Station B. Guidance systems comprising homingsignals transmitters 431 t; receivers 431 r; may be used to bring thetwo bodies into proximity. The depowered HAV-100 aa traversingunderneath bay 428 w may be brought into alignment by means of itstether 50 aa and motorized self-propulsion mechanisms 70 ad, 70 ae. Aflexible U-shaped bracket 432 and suction cups 433 a may be mounted onthe belly-side of bay 428 w. A grappling hook 435 attached to line 436held in a concealed spring loaded self-restraining reel 437; and suctionpads 433 b may be installed on the body 99 aa of HAV-100 aa. Inproximity, raised hook 435 attached to line 436 on HAV-100 aa hitches upwith flexible U-shaped bracket 432 which swung backward; bringing thebody 99 aa of HAV-100 aa closer to the belly of bay 428 w; with thesuction pads 433 a and suction cups 433 b attaching themselves together.Suction cups 433 a may also be configured with flexible holders 434inlaid with vacuuming tubes connected to a vacuum system; and waterspray nozzles for enhancing the suction effects between the suction cups433 a and suction pads 433 b. Other anchoring mechanisms may then bebrought into effect such as pneumatic clamps equipped with locking pins;locking arms; locking bars, etc. to grip and immobilize the HAV-100 aa.

FIG. 2F to FIG. 2H illustrates the sequential phases of an aerial takeoff by HAV-100 aa from docking bay 427 w. Upon release from theanchoring sub-system 430 of FIG. 2D to FIG. 2E; HAV-100 aa detaches anddrops downward, slipping away from Station B (blown by the upstreamwind) before powering up for its next run segment to Station C; affixedto a full length tether line 50 ab (just changed out at joint 229 az)from driven unit 55 ab located on ground level beneath Station B; thebi-directional winch 59 az is activated to turn the HAV-100 around,wherein the bow and stern exchanges position. Joining point 229 az ofthe tether 50 ab on the retract lines 33 az; 33 ay; is moved from thebow, point 227 az (FIG. 2F); to midpoint (FIG. 2G); to the stern, point215 az (FIG. 2H). Windbag 30 aa may then be deployed propelling thedrone downwind of Station B, moving to Station C.

FIG. 2I illustrates the interactive forces generated in a HAV-400. Theprimary forces comprising the flow of wind current; and the load actingon tether line 50 aa; causes generation of resultant forces acting onthe drone causing it to move upwards 438 and backwards 439.

FIG. 3A to 3B illustrates a renewable energy generation sub-system 440.HAV-400 may be connected to driven unit 55 ag for generatingelectricity. FIG. 3A illustrates the possible sequence of the variousstages of lifting flight; from location L1 marked as Start-Of-Run (SOR)point 16 aa; ascending to higher downwind location L2, point 441; thenlocation L3, point 442; until reaching final End-Of-Run (EOR) point, 288aa marked as location L4; prior to depowering; and descending to loweraltitudes with slower winds while being retracted back to location L5,point 443; then location L6, point 444; and then finally back tolocation L1, SOR point 16 aa; where it awaited redeployment. FIG. 3Billustrates driven unit 55 ag connected to drive unit HAV-400 via tether50 ag for producing electricity by means of tether spool 52 ag; gear box53 ag; generator 54 ag; and retract motor 49 ag. Optionally, system 55ag maybe flexibly connected to air-compressors 55 ac; or pumps 55 ap;etc.

FIG. 3C illustrates an aero-electric generation plant and sub-system450. HAV-400 is shown connected to driven unit 55 ac comprising linereel drum 52 ac; gear box 53 ac; air compressor 54 ac; and retract motor49 ac; for producing highly pressured compressed air; which may berouted via pipes 452 for storage in spherical tanks 453 a; orunder-ground storage facilities 453 b (not shown). The stored potentialenergy in compressed air 451 may be used to run air turbine 454 drivengenerator 455 to generate electricity 456 on demand; which may be routedto consumers via cables 457 and transmission towers 458. Optionally itmay be used to do other useful work on demand. It may also be usedtogether with impact induced energy conversion systems.

FIG. 3D illustrates a pumped hydro-power generation plant and sub-system460. HAV-400 may be connected to a driven unit 55 ap comprising linereel drum 52 ap; gear box 53 ap; water pump 54 ap; used with a storedpotential energy system to produce hydro-electricity on demand. Water461 may be moved by pump 54 ap from reservoir 462 at grade to aplurality of elevated reservoirs 463 located at height. Potential energyof stored water 461 from elevated tanks 463 may be used to run waterturbine 464 driven generators 465 to produce electricity 456 on demand.For FIG. 3C to 3D instead of using HAV-400, the drive units may besubstituted by HAV-100 aa. Optionally, instead of directly using HAV-400to run compressor 54 ac or pump 54 ap; power produced by drone HAV-400and generator 55 ag in FIGS. 3A and 3B may be used to run the motorspowering compressors 54 ac of FIG. 3C; or, pumps 54 ap of FIG. 3D.

FIG. 4A illustrates a heavy load lifting sub-system 470 for air-lift ofa plurality of wind-turbines 471 to harness high altitude wind energy.Wind-lifter HAV-400 carries aloft a linear array comprising a multitudeof wind turbines 471 by means of tether 50 at for generatingelectricity. High altitude wind acting on turbine blades 472 mounted onshaft 475 running through turbine housing 473 embedded with stator coils474 drives horizontal shaft 475 which rotates rotor coils 476 to produceelectricity 456, as is known in any wind turbine generators. Verticalshaft wind turbines 477 may also be airlifted. Electricity 456 generatedmay be transmitted by means of cables 478 embedded into load tether 50at; or, control line 46 aa.

FIG. 4B illustrates a variant sub-system 480 wherein an array of windturbines 471; of various sizes mounted in a framework orcarrier-apparatus 480 may be carried aloft at height by means of tether50 at to harness high altitude wind energy. A plurality of such arrays480 of wind turbines 471 may be lifted into high altitude to harnesshigh altitude wind energy. Carrier apparatus 480 may comprise of aninternal lattice work of square shaped supporting struts 479 anddiagonally inclined supporting struts 481; enabling mounting of turbinehousing 473. HAV-400 may be kept in location by means of control lines46 aa and ground based system comprising line reel 52 aa and windingmotor 49 aa. A plurality of bridle lines 21 aa may be used to connectthe tether 50 at with carrier-apparatus 480 at point 410. Optionally, apulley-roller apparatus 482 installed at point 410 may be used to liftor lower the tether line 50 at and array of turbines 471 up or downwithout altering the height of the HAV-400. Such that line 50 at may belooped through apparatus 482; one end bearing the load of wind-turbineswith the other end connected to a ground line reel system used forcontrol line 46 aa comprising line reel 52 aa; winding motor 49 aa.Fixed or adjustable wind vanes 483 may be used to provide properalignment of apparatus 480 relative to wind flow; ensuringeffectiveness, efficiency and productivity of the system.

FIG. 4C illustrates the cross-sectional side view; FIG. 4D illustratesthe cross-sectional view of the motor of FIG. 4C; a counter-rotatingairborne wind-turbine-generator system AWTG-490 h configured with dualrings of rotor coils and rotor magnets; turning the shaft 475 (and rotormagnet 476 h); and yoke 484 (and rotor wire coil 474 h) in two oppositedirections of rotation. Such a twin rotors concept differs in structuralconfiguration from a standard turbine-generator setup comprising: astator wire coil 474 and a rotor magnet 476; or conversely (a statormagnet and a rotor wire coil); with single or dual turbines 472 turningthe shaft 475 in a single direction of rotation as illustrated in FIG.4A and FIG. 4B. To this end wind energy harnessed by means of the dualfront and rear (fore and aft) mounted turbines may be used to producecounter-rotational movements in both rings of the rotor coils. Such thatboth rings of rotors comprising: wire coil 474 h and magnet 476 h arerotating; but in opposite directions to each other; individuallyconnected to and powered by its own dedicated wind-turbine propulsionsub-unit 472 f and 472 a. Fore turbine 472 f may be connected directlyby means of shaft 475 h to the centrally mounted electro-magnet 476 h.Aft mounted turbine 472 a may be directly connected to the shell mountedwire coil 474 h (surrounding magnet 476 h) by means of a yoke 484connected to hub 485. The generator 473 may be protected by externalbody cover 473 h. A variable electrical (or magnetic flux) controller466 may be used to vary the supply of current to the electro-magnet 476h of the generator; and thus vary the production of electricity relativeto the wind power available at the point in time. If the wire coil 474 hrotates clockwise; then the magnet 476 h rotates anti-clockwise. Or,vice-versa. Wherein the speed and movement of the generating surfaces ofboth rotating elements relative to each other may be doubled. Such adouble counter-revolving dynamic surfaces configuration of system 490 henables much higher efficiency and productivity as compared to standardairborne wind turbine generators of FIG. 4A and FIG. 4B. And may be usedto replace them/or used together with them.

FIG. 4E to FIG. 4F illustrates a variant system with twin “flattened”disc-shaped generating surfaces vertically aligned. FIG. 4E illustratesthe side view of a vertically disposed generation system AWTG-490 d;while FIG. 4F illustrates the cross-sectional plan view of FIG. 4E.Wherein the double counter-rotating discs comprising the wire coil 486and magnet 487 may be directly connected by means of shafts 475′; 475″and angular transmission gear mechanism 467 to the fore turbine 472 fand aft turbine 472 a. If the wind energy harnessed is directlytransmitted from the turbines to generator without angular transmissiongear mechanism 467, the generating components may be aligned directlyfacing the wind direction. This incurs undesirable drag forces. Toovercome this shortcoming, the counter-rotating discs may be realignedin a streamlined manner relative to the wind flow as shown. The discsmay also be oriented horizontally; instead of vertically aligned.

FIG. 4G illustrates a variant system AWTG-490 q of FIG. 4C and FIG. 4Dwherein quadruple turbines comprising two sets of twin counter rotatingturbines may be configured in close proximity to each other. The firstfore turbine 472 fw may be connected to the shaft 475 h to power thegenerator. While the second fore turbine 472 fx may be configured to befreely spinning, but turning in a direction opposite to that of frontfore turbine 472 fw. The turbine blades may incorporate/or be embeddedwith generating elements comprising: wire coils 488 and magnets 489. Thefirst fore turbine blades 472 fw may incorporate wire coils 488. Thesecond fore turbine blades 472 fx may incorporate magnets 489. Oncomingwind flow (W) may rotate the blades of first fore turbine 472 fw(powering the shaft 475 h) clockwise; then flows to rotate the blades ofsecond fore turbine blades 472 fx (free-spinning) anti-clockwise. Suchthat when the twin turbines in close proximity counter rotates againsteach other the embedded elements 488 and 489 in the moving turbine rotorblades may generate electricity. The same configuration applies to thefirst aft turbine 472 ay and second aft turbine 472 az. Oncoming windexiting fore turbines 472 fw and 472 fx flows over to rotate the firstaft turbine 472 ay (free-spinning) clockwise; then flows over to rotatethe second aft turbine 472 az (powering the yoke 484) anti-clockwise.Two generation sources comprises: (a) twin rotors of wire coil ring 474h and magnet ring 476 h; (b) embedded wire coils 488 and magnets 489present in the turbine blades 472 fw; 472 fx; 472 ay; 472 az.

Likewise FIG. 4H illustrates twin turbine rotors 472 f (fore) and 472 a(aft) mounted on fixed pillar 469 and adjustable pillar 469 m; whichcounter rotates against each other to produce power by means of embeddedwire coils 488 and magnets 489. A swivel joint 468 may be incorporatedinto the top of fixed pillar 469 near generator module 473; whilemovable pillar 469 m may be shifted by means of a motor in asemi-circular arc shaped base 459 c configured into concrete pedestal459. This enables shifting of the turbines to face the wind. Twogeneration sources comprises: (a) conventional stator 474 and rotor 476assembly of generators 473; (b) wire coils 488 and twin magnets 489embedded into the turbine blades 472 f and 472 a.

FIG. 4I illustrates the sectional front view of a variant version ofvertical axis turbine 477 v wherein, a plurality of counter-rotatingsections of said turbine may be configured to operate as a single unit477 v for producing electricity by means of twin rotors poweredgenerators 474 r; 476 r; and disc generators 486 r; 487 r mechanisms;using both vertical axis generating elements comprising: rotor wirecoils 474 r; rotor magnets 476 r; and flat discs of rotor wire coils 486r; and rotor magnets 487 s. The entire apparatus 477 v may be set up onfixed pillars/or, it may be lifted into high altitude by means of tether50 at affixed to HAV-400 wind crane. Section A and C may be configuredto revolve clockwise; while section B and D may be configured to rotatein an anti-clockwise direction. The vertically aligned rotor shaft 475 vran from the topmost vertical axis generating elements 486 r; 487 s(above section Ag) to the bottom most generating elements 486 r; 487 s(below section Dg). Shaft 475 v bore the entire weight of apparatus 477v. An orifice 459 may be configured into the magnet discs 487 s and 487r to enable passage of vertical shaft 475 v. Electricity generated maybe routed via tether-cable 478.

The vertical axis generating elements may comprise of: rotor shaft 475 vaffixed with wire coils 474 r; and rotor casings 477 c affixed withmagnets 476 r. In section A and C; rotor shaft 475 v driven by theturbine blades may be configured to turn in a clockwise direction. Insection B and D; shaft 475 v may be integrated with a layer (ring) ofwire coil 474 r; surrounded by a layer (ring) of magnet 476 r integratedinto rotor casings 477 c of turbine blades 477. Casing 477 c isequivalent to yoke 484 of FIG. 4C and FIG. 4D. The turbine blades 477may be configured to turn casings 477 c and layer (ring) of magnet 476 rin an anti-clockwise direction. This counter revolving movement providedby the (a) rotating shaft 475 v to the rotor wire coils 474 r(clockwise); and the (b) rotating turbine casing 477 c to the rotormagnet rings 476 r (anti-clockwise) may be used by the vertical axisgenerators 477 v to produce electricity.

The horizontally aligned disc generating elements AB; BC; CD; configuredin between sections A; B; C; D; may also be used to produce electricity;from the counter rotational movement of the rotor wire coiled discs 486r and the rotor magnet discs 487 r. Vertical axis disc generator AB usesthe clockwise movement of section A turbine to drive the wire coil disc486 r; and the anti-clockwise movement of section B turbine to drive themagnet disc 487 r. The topmost and bottom most discs generators Ag andDg may comprise of: rotor wire coil discs 486 r and stator magnet discs487 s. Two generation sources comprises: (1) wire coils 474 r; magnets476 r; (2) rotor wire discs 486 r; rotor magnet discs 487 r; andconventional stator-rotor setup 486 r; 487 s.

An airborne ecosystem 500 for extraction of high altitude wind energiesfor generation of renewable energies; comprising the integration of: (1)an aerial system of heavy lifting drones HAV-400; with (2) heavy liftedloads. Wherein said heavy lifting apparatus comprises HAV-400 windcranes. Said heavy lifted loads comprises: (a) wind turbines: 471; 477v; 490 h; 490 d; 490 q; 500 b; 500 c; 500 d; multi-stagedcounter-rotating wind turbines 500 a; (b) a high altitude wind energyharvesting system 510 a comprising airborne Station X, Station Y; (c)and an improved system 76 aa with a multitude of flying windbags 30 apspearheaded by a drone HAV-400; a drone HAV-100 aa. This ecosystem 500may be illustrated by FIG. 5A to FIG. 5M; in combination with FIG. 4A toFIG. 4G; FIG. 4I; FIG. 6A to FIG. 6N; FIG. 6P to FIG. 6Q; and FIG. 8B.

FIG. 5A to FIG. 5M illustrates a variant system 500 a to 500 d ofAirborne-wind-Turbine-Generators-500 a herein designated as AWTG-500 ato 500 d; lofted into high altitude by means of HAV-400 wind-cranes toharness and to harvest high altitude wind energy. TheAirborne-wind-Turbine-Generators AWTG-500 a being lifted may beconfigured to be vertically disposed; or inclined at an angle relativeto the wind direction (refer FIG. 5C; FIG. 5D; FIG. 5J; FIG. 5M). Thissystemic variability may be required to adjust to changes in windspeed/energy; turbulence; loading; for operational purposes andpracticability of application. At a certain angle of incline, wind-liftcaused by the upward thrust of the wind current on the AWTG-500 a mayreduce its weight; or load on the HAV-400; thus partially balancing outthe weight of AWTG-500 a.

FIG. 5A to FIG. 5D illustrates a system comprising of a multi-stagedcounter-rotating airborne wind turbine generator AWTG-500 a mounted on asingle plane; with multiple rings of generating mechanisms 491comprising: concentrically arranged rings of turbines blades 492; rotorwire coils 493; rotor magnet coils 494. One rotating circular ring 491mounted inside/or outside of another rotating circular ring 491. FIG. 5Aillustrates the front view of a vertically lifted wind turbine 500 a;FIG. 5B illustrates the cross-sectional plan view of FIG. 5A. FIG. 5Cillustrates a side view of FIG. 5A; while FIG. 5D illustrates a sideview with the turbine lifted at an inclined position.

The structural configuration of conventional wind turbines comprisesstators and rotors. Wherein the configuration of present inventioncomprises: dual rotors; no stators. Dual rings of rotor coils and rotormagnets; turning the generating mechanisms in two opposing directions ofrotation. To this end wind energy harnessed by means of such dual rotorsmay be used to produce counter-rotational movements in both rings of therotor coils. With reference to FIG. 5A to FIG. 5B viewed from the centerhub 496 moving towards the periphery, the outer-most edge 501; theconfiguration of AWTG-500 a may be described as follow: (a) Stage 1turbine-generator ring 491 a comprising: a circular ring of turbineblades 492 a; configured with a ring of rotor wire coil 493 a at theouter edge; and a ring of rotor magnet 494 a surrounding a stator wirecoil 495 s at the hub 496. (b) Stage 2 turbine-generator ring 491 bcomprising: a circular ring of turbine blades 492 b affixed to a ring ofwire coil 493 b at the outer edge; and a ring of magnet 494 b at theinner edge. (c) Stage 3 turbine-generator ring 491 c comprising: acircular ring of turbine blades 492 c bearing a ring of wire coil 493 cat the outer edge; and a ring of magnet 494 c at the inner edge. Centralhub housing 496 may be configured with conventional rotor magnet 494 aand stator wire coil 495 assembly to produce electricity. While thegeneration mechanism at the circumference of apparatus 500 a maycomprise of a ring of rotor wire coil 493 c and stator magnet ring 497s. Rotor wire rings 493 and rotor magnet rings 494 rotates and moves inextended guide sleeves 498 of frame-work girders 499; keeping them inposition. Roller bearings and ball bearings may be used whereapplicable.

The whole wind-turbine-generator apparatus 500 a may be slotted into andsecurely mounted in a circular body clamp 501; supported by a frameworkcomprising girders 499; struts 502; etc. Any number of girders 499 andstruts 502 may be used to support the apparatus as desired. Circularbody framework 501 may be configured as a clamp mechanism grippingtightly onto apparatus 500 a. Hub 496 and body clamp 501 may beconfigured with provisions for line (21 aa to 21 ad) attachments such aslifting rings 501 c for use with lifting clamps and hooks; winches 59 aa(for line adjustment); rudders 69, rudder-fins 84 aa; fins 85 aa andwinglets 85 aa; for computerized 503 directional control andorientation. Electricity may be generated when one power generating ring491 comprising: a ring of turbine blades 492 mounted with a ring ofrotor wire coil 493 and a ring of rotor magnet 494 at each end; rotatesagainst the counter rotating components of another ring(s) 491 mountedadjacent to it in close proximity. Or, rotates against fixed statorcomponents such as the stator wire coil 495 located at the central hub496; and the outermost stator magnet ring 497 located at the edge ofapparatus 500 a. Optionally, stage 3 turbine blades 492 c may beconfigured with rings of magnets 494 c at both the inner and outeredges; surrounded by a stator wire ring 497 at the outermost edge ofAWTG-500 a. Such flexibility of configuration may be used to optimizedesign and efficiency.

The stage 1 turbine-generator ring 491 a; and stage 3 turbine-generatorring 491 c may be configured to rotate in the same direction, with stage2 turbine-generator ring 491 b (located in between stage 1 and 3)configured to rotate in the opposite direction. For example: if stage 1and stage 3 are configured to rotate clockwise; stage 2 shall beconfigured to rotate anti-clockwise. Or conversely configured. Such acounter-rotational structural configuration enables doubling of therelative speed of rotation between the stage 2 turbine-generator 491 b(anti-clockwise); and that of stage 1 turbine-generator 491 a(clockwise); and stage 3 turbine-generator 491 c (clockwise). Andvice-versa. Thus rotational movement and relative speed between thestage 2 turbine-generator 491 b (rotating anti-clockwise); and that ofstage 1 and stage 3 turbine-generators 491 a; 491 c (rotating clockwise)may be doubled. This may increase the efficiency and productivity (e.g.doubled power generating capacity) of theAirborne-wind-Turbine-Generator-500 a in producing renewableelectricity. Multiple stages of counter-rotating AWTG-500 a in excess ofthree stages (as illustrated); for example: five stages; ten stages;etc. may also be configured for use.

FIG. 5C illustrates the side view of an AWTG-500 a lifted in a verticalposition; while FIG. 5D illustrates the side view of an AWTG-500 alifted in an inclined position by means of HAV-400 wind crane. Tetherline 50 aa and a plurality of bridle lines 21 aa may be used to enablelifting of the units into a suitable height for harnessing high altitudewind energy. FIG. 5E to FIG. 5G illustrates the front view of variantAirborne-wind-Turbine-Generator 500 b; 500 c; 500 d. FIG. 5H illustratesthe cross-sectional side view 5H-5H; while FIG. 5I illustrates thecross-sectional side view 5I-5I. FIG. 5H and FIG. 5I illustrates twopossible arrangements in which the apparatus as shown in FIG. 5E to FIG.5G may be configured. Wherein AWTG-500 b; 500 c; 500 d; may beconfigured as illustrated in FIG. 5H (single plane), FIG. 5C and FIG.5K. Or arranged side-by-side in a port and starboard configuration asillustrated in FIG. 5I; FIG. 5J (dual plane); and/or in an over-underconfiguration (inclined lift); if FIG. 5J is lifted in an inclinedposition as illustrated in FIG. 5D and FIG. 5M.

The apparatus may be configured to generate electricity by means of acentrally located hub 496 in the middle; and at the periphery 497 e; 497f; 497 g. Hub 496 may comprise of rotor magnet ring 494 e; 494 f; 494 g;and stator wire coil 495 e; 494 f; 494 g/or standard stator 474 androtor 476 coils (refer FIG. 4A). The generation mechanism at thecircumference of the turbine may comprise of a ring of rotor wire 493 e;493 f; 493 g and a ring of stator magnet 497 e; 497 f; 497 g. The innerring of rotor wire 493 e; 493 f; 493 g mounted at the tip of the turbinerotors 492 e; 492 f; 492 g revolves around an outer coiled ring ofmagnet 497 e; 497 f; 497 g; mounted in a ring at the outermost edge 473e; 473 f; 473 g. Optionally in a vice versa arrangement; theconfiguration or location of generating mechanism comprising: statorwire ring 495 and rotor magnet ring 494 may be swapped.

FIG. 5E, FIG. 5F and FIG. 5I illustrates a system wherein generatingmechanisms comprising rings of rotor wire 493 f; 493 g and rings ofcoiled stator magnet 497 f; 497 g; may be integrated into a single unitprotected by generator housing 473 f; 473 g. FIG. 5A illustrates aconfiguration comprising exposed individual rings of rotor magnet 494;and coiled stator wire 493 components. FIG. 5H illustrates the side viewof a standard single turbine-generator 500 b; 500 c; 500 d; configuredwith rotor 494 e and stator 495 e assembly in the central hub 496 e. Thering of rotor blades 492 e may be affixed with a ring of rotor wire 493e at the edge; surrounded by an external ring of stator magnet 497 e.

FIG. 5I illustrates a variant configuration of FIG. 5H wherein dualunits of turbine-generators 500 b; 500 c; 500 d; may be configuredside-by-side, vertically oriented and aligned in a fore and aft position(refer FIG. 5J) or in a port-starboard configuration and in closeproximity to each other, facing the wind. The blades of twin turbines492 f (fore); 492 g (aft) may be configured to counter-rotate againstone another. The counter-revolving turbine blades 492 f; 492 g mayincorporate/or be embedded with power generating elements comprising:rotor wire coil 488 and rotor magnets 489. For example: if the foreturbine blades 492 f embedded with wire coils 488 rotates clockwise; theaft turbine blades 492 g embedded with magnets 489 shall rotate in ananti-clockwise direction. These embedded rotor wire coils 488 and rotormagnets 489 present in counter-revolving turbine blades 492 f and 492 gmay also be used to produce electricity. Just like the standard rotor494 f; 494 g; and stator 495 f; 495 g assembly in the central hub 496 f;496 g.

In this configuration, electricity may be produced from three generationmechanisms comprising: (a) standard rotor magnet ring 494 f (and 494 g)and stator wire coil 495 f (and 495 g) in the hub 496 f (and 496 g); (b)rotor wire coil ring 493 f (and 493 g); and stator magnet ring 497 f(and 497 g) at the circumference; and (c) counter-rotational movement ofwire coils 488 and magnets 489 embedded into turbine blades 492 f and492 g. Electricity 456 produced from all of the three above points ofgeneration may be collected and channeled into tether-cables 478 to amooring buoy 508 for conveyance to processing plants on floatingplatforms.

FIG. 5J illustrates a variant version of FIG. 5I wherein twin units ofATG-500 a (mounted on dual planes) may be combined together in aside-by-side/or, in an over-under configuration to function operably asa single unit. Incorporation of embedded rotor wire coils 488 and rotormagnets 489 into turbine blades 492 as illustrated by FIG. 5I may enableimproved productivity and efficiency. The apparatus may be lifted intohigh altitude in a vertical/or inclined position by means of HAV-400wind crane using a plurality of bridle lines 21 aa and tether line 50aa. FIG. 5K illustrates system 500; showing the front view of awind-crane HAV-400 lofting a plurality of vertically disposed turbinegenerators 471; AWTG-500 a; 500 b; by means of tether 50 aa facing theoncoming wind. FIG. 5L illustrates a customized storage rack-container504 with partitioned slots 505 for keeping the ATGs-500. Demobilizedunits may be lowered and slotted back into rack 504.

FIG. 5M illustrates system 500; wherein, an inclined AWTG-500 b may belifted into high altitude by means of a HAV-400 wind-crane. The tether50 aa may be linked to bridle lines 21 aa; 21 ab; 21 ac; 21 ad; atcommon joint 506; with camera 507 attached. Lines 21 aa to 21 ad may beattached to the external framework 501 of turbine-generator 500 b bymeans of lifting lugs and rings 501 c and their lengths adjusted bymeans of winches 59 aa. Electrical power generated may be routed bymeans of cable-tether 478 to reel system 52 aa mounted on a seabornemooring buoy 508; which may in turn be routed by means of submarinecables 457 u to floating electrolyzer plants 509 s abroad FPSO vessel511 for producing hydrogen gas. Cable 457 u may also route theelectricity to a land based hydrogen gas generation plant 509 t.Specially configured Floating Production Storage Offloading (FPSO)vessels 511; sited proximate to buoy 508 provides a floating platformfor producing hydrogen gas/or for other means of energy conversions;storage; transfer of products to seaborne carriers; etc. The renewableelectricity generated may also be channeled by means of submarine cables457 u to land based transformer stations, overhead cables 457 and towers458 for transmission to consumers; /or to land based electrolyzer plants509 t for conversion, storage, transfer, etc. Such electrolyzer plants509 s may also be sited on fixed leg platforms 290 aa/or borne by mobilefloating production rigs and flatbed vessels comprising:semi-submersible platforms 292 aa; flatbed platforms 293 aa; inflatablefloating bodies 294 aa; anchored to the seabed piles 545 by means ofsubsea cables 295 aa; supported by mother ships 289 aa; factory ships296 faa; tankers 296 taa; etc. Such mobile floating platforms/or bodiesmay also be moored by means of lines 512 to floating buoys 508; whichmay in turn be secured by means of subsea cables 295 aa to underseapillars 545; piles 562; beams 563; plugs 564; etc. (Refer: System 300 ofFIG. 13I; FIG. 13D of U.S. Pat. No. 8,963,362). The external frame ofthe AWTG-500 b may be equipped with computerized 503 directional controlsurfaces comprising: rudder-fins 84 aa; fins and winglets 85 aa; whichmay be manipulated to orientate the module into a desirable; optimalposition relative to the wind direction and altitude. Computerizedsystem 503 abroad may be configured for total operational control ofAWTG-500 b comprising: self-alteration, self-alignment and automatedadjustment of system 500 b's orientation and position relative to thewind direction; wind speed; optimized energy production; used to monitorAWTG-500 b's system performance; faults and deficiencies with the helpof cameras 507. And for liaison and feedback with surface based/orground based computerized smart control systems such as the DCS;integrated with Artificial Intelligence (AI).

FIG. 6A to FIG. 6N illustrates an airborne high altitude wind-energyextraction system 510 a for deploying a plurality of windbags 30 aa.FIG. 6O illustrates a deep-sea-diving ocean-energy extraction system 510u for deploying a plurality of water-bags 40 aa. Systems 510 a and 510 umay be deployed together in the combined wind and water energiesextraction plant 300 (previously disclosed in FIG. 13I of U.S. Pat. No.8,963,362)—a marine eco-system specially configured for the productionof renewable energies. FIG. 6A to FIG. 6N illustrates an airborne system510 a; while FIG. 6O illustrates a seaborne system 510 u; wherein saiddisclosure may comprise parallel systems to the riverine hydro-energyextraction plant 310 (previously disclosed in FIG. 14A to 14G of U.S.Pat. No. 8,963,362).

However, compared to riverine system 310 executed on land; airbornesystem 510 a and deep-sea diving system 510 u are much more complex anddifficult; and operates in an occupational environment more hazardousthan run of the river systems. Requiring the use of apparatus,equipment, systems, methods and techniques as disclosed in FIG. 6A toFIG. 6N. The airborne system 510 a requires much more complex lightweight components, HAV-400; air-bridges 429 p; 429 r; radio-frequencyactivated sub-systems. While the seaborne system 510 u requiressemi-submersible platforms comprising: upstream surface Station U;downstream bottom Station V; supporting surface Station W; secured bycables 295 aa to pillars 545 piled into the seabed 537; or, to suctioncups 550 affixed to the sea-floor 537; submarine boats 220 aa; personalsubmersible vehicles 220 aa. The combined airborne system 510 a andseaborne system 510 u may also be integrated with other components ofthe marine ecosystem 300 comprising: fixed leg platforms 290 aa; mobilefloating production rigs and flatbed vessels; semi-submersible platforms292 aa; floating flatbed platforms 293 aa; inflatable floating bodies294 aa; mooring buoys 508; electrolyzer plants 509 abroad FPSO 511;anchored by means of undersea cables 295 aa to pillars 545; piles 562;beams 563; plugs 564; etc. in the seabed 537 and seamounts 555;supported by mother ships 289 aa; factory ships 296 faa; tankers 296taa; etc. deep-sea diving and operation components; sonar activatedsub-systems; etc. including other hi-tech equipment such as advancedArtificial Intelligence computers; specialized equipment and much morecomplex sub-systems than the riverine extraction plant 310. Actionablesolutions much more difficult to execute than the prior art disclosure.Relevant components disclosed herein may also be adapted for use withsystem 310.

FIG. 6A illustrates an overall view of the airborne high altitude windenergy extraction cum power generation system 510; whereas, FIG. 6B andFIG. 6C illustrates more detailed arrangements of Station X, 429 p(Start-of-Run) SOR point 16 aa; and Station Y, 429 r (End-of-Run) EORpoint 288 aa. For ease of description these two points may be referredto as Station X and Station Y. Wherein, both Stations X and Y may belofted; carried up into high altitude by means of a plurality of HAV-400wind-cranes. Optionally, tethered 46 aa HAVs-45 aa; balloons;airships-45 aa; aerostats-45 aa and blimps 45 aa may also be used.Station X may be located upwind of Station Y. Station Y may be locatedat the same altitude as Station X; or Station Y may be located at ahigher altitude than Station X; enabling windbags 30 aa to engage windof much higher speed and energy as they ran from Station X (SOR) toStation Y (EOR). One pair of guide lines (304 ap′; 304 ap″) forms acomplete loop from Station X to Station Y for power run of windbags 30ap; and from Station Y back to Station X (304 ar′; 304 ar″) forretraction, return, retrieval of windbags 30 ar. A multitude of suchpairs of guide-lines (forming lane A, lane B, lane C, etc.) may beconfigured running to and from Station X and Station Y. With thewindbags 30 aa used and reused repeatedly within the loop of runninglanes (A; B; C). Generating renewable energies from High Altitude WindPower.

Windbags 30 ap may be flexibly connected to a pair of guide lines marked304 ap′ and 304 ap″ (which forms aerial runway Lane A) by means of apair of swivel holding rings 308 ap′ and 308 ap″. At the air-bridge 429p of Station X (a more advanced form of work platform 47 aa) windbags 30ap with inflated ring 22 ap and air-ribs 277 ap may be released throughthe SOR gates 520 p′; 520 p″; running from Station X to Station Y alongLane A formed by guide lines 304 ap′ and 304 ap″; pulling tether 50 aa;powering generator 55 ag. At the End-of-Run phase near Station Y, airmay be released from the exhaust port 532 of pressure control sub-system530; deflating ring 22 ap and air-ribs 277 ap. Sub-system 530 may beactivated by means of (RF) radio frequency transmission from a proximitytransmitter 299 raa located on work bridge 429 r to receiver antenna 534(refer FIG. 6K; FIG. 6L). The collapsed, depowered windbag 30 ar may bereleased through the EOR gates 520 r′; 520 r″; of air-bridge 429 rStation Y. The returning windbag 30 ar may be retrieved by means oftether 50 ar wound in by line reel 52 aa and retract motor 49 aa; viaretraction guide lines 304 ar′ and 304 ar″; moving from Station Y toStation X.

FIG. 6D illustrates a much more detailed arrangement of Station X, thanFIG. 6B for launching windbags 30 ap at air-bridge 429 p. While FIG. 6Eillustrates a much more detailed arrangement of Station Y, than FIG. 6Cfor depowering windbags 30 ar; and for their return to Station X. FIG.6D and FIG. 6E also illustrates details of the gated sub-system 520 pand 520 r (refer FIG. 6H to FIG. 6J) at the SOR and EOR phases forpassage of windbags through these anchoring points. Wherein saidplurality of windbags 30 aa are used for generation of power; returnedto the starting point; reused and recycled repeatedly in a closed loop.

FIG. 6D illustrates the detailed layout of the air-bridge 429 p ofStation X for launching windbags 30 ap. This is the Start of Run (SOR)point 16 aa where incoming windbags 30 ap are prepared; readied fordeployment; and launched for a power generating run from Station X toStation Y. Collapsed incoming windbags 30 ar returning from Station Yarrives by means of dual returning guide lines 304 ar′ and 304 ar″; withthe port and starboard holding rings 308 ar′ and 308 ar″ in closeproximity to each other due to the collapsed state of windbag 30 ar. AtStation X the pair of guide lines 304 ar′ and 304 ar″ may be enjoined toa pair of “Y”-shaped solid state frames 515 p′; 515 p″ at joints 514 r′;514 r″. Said port and starboard guide lines 304 ar′ and 304 ar″ may beenwrapped/or embedded inside of a thick solid state frame 515 p′ betweenthe points 514 r′ to 514 p″; and frame 515 p″ between the points 514 r″to 514 p″. The “Y”-shaped frames 515 p′; 515 p″ may be held in positionby the dual banks of the gated sub-system 520 p′; 520 p″. Components 521and 522 of sub-system 520 p may be configured along the windbags 30 aprun-way (Lane A) formed by port and starboard guide lines 304 ap′ and304 ap″ embedded in frames 515 p′ and 515 p″. Dual guide lines 304 ap′;304 ap″ in turn forms an airborne run-way for the guided flights ofwindbags 30 ap; which for reference purposes may be designated as: “LaneA”; “Lane B”; “Lane C”; etc. Said “Y” shaped frames 515 p′; 515 p″ maybe spread out reflecting the actual diameter (e.g. 2 m) of the inletport ring 22 ap of the inflated windbag 30 ap as configured.

Solid frame 515 p comprises a component of the guide lines 304 apsystem. It does not form part of the structure of Station X or Y. Guidelines 304 ap running from Station X to Station Y provides a guidedaerial running pathway for windbags 30 ap; pulling tether 50 ap togenerate power by means of generation system 55 ag. Returning guidelines 304 ar running from Station Y to Station X provides a means forretrieving depowered windbags 30 ar. Retracted by means of tether 50 arwound back by spool 52 ar and motor 49 ar. Said guide-lines 304 aasystem forms a round loop from Station X to Station Y; then back againfrom Station Y to Station X. In this loop windbags 30 aa rotates; goingfrom one phase to another; from one cycle to another repetitive cycle.

Though solid frames 515 p and 515 r does not comprise part of thestructure of Station X; Y; it may be flexibly and securely connected tosaid structures by means of gated sub-system 520 and affixedholder-stands 525. At station X, as the windbag 30 ar moves past point514 r′; 514 r″; frame 515 p′; 515 p″ spreads out and widens the “Y”shaped gap in between the two incoming guide lines 304 ar′; 304 ar″.Cover 536 may be removed from the external of windbag 30 ar and/orretract line 33 ar disengaged from clip 533 at point 31 aa by means ofrobotic appendages 522 comprising arms 526; hands 527; fingers 528; andthumbs 529. Depowered windbag 30 ar is freed and opens up. Pressurizedair may be injected into inlet port 531 of controller 530 by means ofhand held (robotic limbs 522) compressed air nozzle 535; inflating inletport ring 22 ap and air-ribs 277 ap. Windbag 30 ap passes through theelectronic gated sub-system 520 p before being released to fly toStation Y. Sub-system 520 p and 520 r provides the two main contacts andonly anchoring points securing guide lines 304 aa in between Station Xand Station Y. Sub-system 520 p allows safe and secure passages ofwindbags 30 ap through the anchored guide-lines 304 ap′; 304 ap″ at theSOR point 16 aa. Sub-system 520 r allows safe and secure passages ofwindbags 30 ar through the anchored guide-lines 304 ar′; 304 ar″ at theEOR point 288 aa. Ensuring positive physical contact between the guidelines (304 ap and 304 ar) and the air-bridges (429 p and 429 r).

FIG. 6E illustrates a more detailed layout of the air-bridge 429 r ofStation Y for depowering windbags 30 ap. This is the End of Run (EOR)point 288 aa where incoming windbags 30 ap are depowered and processedfor return to Station X (SOR). The port and starboard guide lines 304ap′ and 304 ap″ joined the solid frames 515 r′ port side and 515 r″starboard side at points 514 p′ and 514 p″; thereafter the twin piecesof solid frame 515 port and 515 starboard may be curved to convergetogether in proximity to each other. Securely held in position by lockedgate sub-system 520 r affixed to holder-stands 525 which forms part ofair-bridge structure 429 r. After the gated sub-system 520; solid frames515 may be curved to bend downwards; joining port guide-line 304 ar′ atpoint 514 r′ and starboard guide-line 304 ar″ at point 514 r″.Guide-lines 304 ar′ running from Station Y may be connected to the portsolid frame 515 r′ of Station X air-bridge 429 p at point 514 r′; and304 ar″ connected to the starboard solid frame 515 r″ at point 514 r″.

In proximity to EOR Station Y air-bridge 429 r, incoming windbag 30 apmay be depowered by means of apparatus 530; activated by RF signals fromapparatus 299 raa. Inlet port ring 22 ap and air-ribs 277 ap collapsed.Gear box 53 ag of generator 55 ag may be freed. The collapsed windbag 30aa may be routed to apparatus 520 ar where it passes through theplurality of gates 521; 522 one at a time till it reaches the downwardbending portion of frame 515 r′; 515 r″. The returning windbag 30 ar isreeled in by means of tether 50 ar and retract motor 49 ag; from StationY to Station X.

Optionally, after exiting gated sub-system 520 r, holding ring 308 ap′may be shifted from port guideline 304 ap′ to starboard guideline 304ar″ by means of robotic limbs 522; prior to the return journey fromStation Y to Station X. Upon arrival at Station X, this maneuver may bereversed. The holding rings 308 ar′ may be shifted from the port frame515 p″ holding guideline 304 ar″ back to starboard frame 515 p′ holdingline 304 ap′; prior to entering gated sub-system 520 p. Such a maneuveravoids interference of lines 50 ap and 50 ar between a multitude ofrunning and returning windbags 30 aa.

FIG. 6F illustrates an optional configuration wherein twin retract lines304 ar′ and 304 ar″ may be combined together and merged into a singleline 304 ar for returning depowered windbags 30 ar from Station Y toStation X. Such a structural configuration eliminates problems of lineinterference; entanglements; knots formation; etc. between lines 50 apin power run and line 50 ar in retraction phase. Because multiplewindbags and tether lines 50 ap; 50 ar may be moving to and fro betweenStation X and Y along a single lane A at any one point in time. Andalong any of the other lanes B; C; D; etc. To this end the dual piecesof “Y” shaped solid frame 515 r′; 515 r″ may be merged into one piece515 r at the confluence of the two split forks 515 r′ and 515 r″ atStation Y. Apparatus 515 p′; 515 p″ may be similarly modified at StationX. At Station Y, upon outgoing windbags 30 ap having cleared the gates520; robotic limbs 522 may be used to effect the switching of the swivelrings 308 ap′ and 308 ap″. From the forked frame 515′ and 515″ holdingguide lines 304 ap′ and 304 ap″; over to the merged frame 515 r holdinga single combined guide line 304 ar. This process may be reversed atStation X wherein, depowered incoming windbags 30 ar may be transferredfrom merged portion of frame 515 r holding line 304 ar; to the forkedportion of frame 515′ and 515″ holding lines 304 ap′ and 304 ap″ bymeans of robotic limbs 522. Readied and prepared for the power up phase;passed through the gated sub-system 520; and put on hot standby.

FIG. 6G illustrates use of a tall relief feature/or topographicallyadvantageous geological features like for example: a high mountain top516 adapted as a high altitude ground Station G. The relief 516 may besuitably modified, converted and configured with structural features 516m; for use as a platform (Station G) for launching windbags 30 ap to anairborne air-bridge 429 r (Station Y) supported by a plurality ofHAV-400 wind-cranes. Ground Station G may replicate Station X of FIG. 6Ato 6D; except that it may be sited on solid ground at a high altitude(e.g. 2 km). It may also comprise of a fixed platform 517 configuredwith flexibly adjustable side extensions 517 x which may be moved aroundwhenever needed to face the wind direction for optimized wind energycapture; extraction and renewable energy production. Motorized mobileside extensions 517 x supported by beams 518 may provide extendedlength; increasing the useful work area. Likewise, an air-bridge stationsuspended in between a plurality of mountain peaks may also be usedtogether with an airborne air-bridge (Station Y).

FIG. 6H to FIG. 6J illustrates components of sub-system 520 comprisingmechanical clamps 521 and robotic limbs 522 for working in anenvironment fraught with extremities—high altitude and deep-sea workstations. FIG. 6H illustrates a mechanized hydraulic clamp cum roboticholder 521 for securing a guide-line 304 aa embedded inside a solidstate frame 515. The two piece clamp 519 a and 519 b may be activated bymeans of mechanized push rods 523 using hydraulic or pneumatic pressurefrom a pump 524 a and reservoir 524. Clamps 519 a and 519 b may includemagnetized locks to maximize locking hold. Apparatus 521 may be securelyaffixed to holder-stand 525 which forms part of the air-bridge structure429 p; 429 r of Station X and Station Y.

FIG. 6I illustrates a side view; while FIG. 6J illustrates a front viewof a variant apparatus 522 of sub-system 520. Mechanical limbs/orappendages 522 may consist of touch sensitive activated mechanismsintegrated with computerized-mechanized robotic limbs/or appendages 522comprising: robotic arms 526 (lower arm 526′; upper arm 526″); hands527; fingers 528; and thumbs 529; integrated with electronic eyes(cameras 509) and artificial intelligence (AI). The figures illustratesrobotic limbs 522 which may be configured with 4 fingers 528 and twothumbs 529; the robotic limb 522 securely holding a thick solid stateframe 515 with a guide-line 304 aa embedded inside. Two thumbs pressingon the four fingers provides superior grip and better hold than a singlethumb; with the thick solid frame 515 providing a larger area and muchbetter holding grip than a single strand of line 304 aa. Frame 515 maycomprise of: glass; fiber-glass; plastics; carbon-fibers; metal; etc.Similar robotic limbs 522 different in arrangement and form may also beconfigured to do useful work. Such artificial robotic limbs mimickingthe extreme dexterity of the human limbs integrated with cameras andcomputerized Artificial Intelligence provides the best equipment andtools required to perform repetitive menial tasks in dangerousworkplaces. Such as high altitude flight and deep sea diving, working inan environment fraught with extreme difference in pressure, temperatureand oxygen deficiency. Where prolonged exposure may not be tolerated byhuman bodies. Apart from sub-system 520, the computerized-mechanicalrobotic limbs 522 comprising: robotic arms 526; hands 527; fingers 528;thumbs 529; may also be used for performing other delicate tasks on theair-bridge 429 p and 429 r; Station X and Station Y; used in support ofother components of present invention and parent U.S. Pat. No.8,963,362.

Gated sub-system 520 may comprise 3 individual pairs of gate apparatus521 and/or 522 configured directly opposite each other along Lane A. Oneapparatus mounted on each side of the solid state frame 515′; 515″embedded with guide lines 304 aa′; 304 aa″; each pair of apparatusarranged one facing the other; aligned along the port side 515′ and thestarboard side 515″ of said gate 520. Spaced out at an optimum distance;a multitude of such pairs of apparatus 521 and/or 522 greater than 3 innumber (maybe up to 10) may be configured; in order for the sub-system520 to work efficiently. A synchronized sequence of opening and closingsaid electronic gates 520 enables phased passage of the swivel holdingrings 308 aa (affixed to windbags 30 aa) through the individualapparatus 521 or 522 of gates 520 p; 520 r. One gate at a time. Thefirst gate to open being gate 1; with gate 2 and 3 closed. Then withgate 1 and 3 closed; gate 2 opens. Then with gate 1 and 2 closed; thelast gate, gate 3 opens. Then with all the gates closed, the sequencestarted over again for a refreshed “new” incoming windbag 30 aa.

FIG. 6K illustrates a puffed up windbag 30 aa with inflated inlet portring 22 ap and air-ribs 277 ap; outfitted with apparatus 530; a pair ofswivel holding rings 308 ap′; 308 ap″ at the sides; and bag cover 536with retract line 33 ar at the rear. FIG. 6L illustrates a computerizedelectronic air pressure control sub-system 530 for controlling theinflation and automated deflation of ring 22 ap and air-ribs 277 ap. Airmay be pumped into the inlet port 531 by means of a hand held (roboticlimb 522) air nozzle 535 to inflate windbags 30 ap prior to beingdeployed. Equipped with radio frequency (RF) activated depressurizingsystem, controller 530 may be activated by means of RF transmitter 299raa and receiver antenna 534 to deflate windbags 30 ap via exhaust port532 as it approaches in proximity to gated sub-system 520 r of StationY. Flexible antenna 534 may be integrated into ring 22 ap; or windbag 30ap. Transmitter 299 raa may be mounted on air-bridge 429 r. Apparatus530 may also be used for RF activated depowering (299 raa; 534) of theoverall airborne wind power generation system 510 in time of emergency:e.g. approaching storms; faulty equipment; emergency shut down anddemobilization of the whole plant, etc.

FIG. 6M illustrates a collapsible-extendable light weight cover 536 forkeeping the depowered windbags 30 ar in a collapsed form for passagefrom Station Y back to Station X. The cover 536 may be extended overwindbags 30 ar by means of robotic limbs 522 comprising robotic arms526; hands 527; fingers 528; and thumbs 529; as the windbags 30 arpasses through the gates 520 r of Station Y. At Station X, as windbag 30ap approaches gate 520 p; cover 536 may be collapsed and air injectedinto port 531 by means of hand-held (robotic limbs 522) air nozzle 535;inflating the ring 22 ap, air-ribs 277 ap. Windbag 30 ap passes throughgate 520 p and is ready for the power run from Station X to Station Y.Optionally, at Station Y, a short retract line 33 ar (aft) affixed tothe apex 32 aa of windbag 30 aa may be pulled by robotic limbs 522 andsecured to joint 31 aa (fore) by means of a spring-loaded clip 533;keeping bag 30 aa in a depowered state. Joint 31 aa being the attachmentpoint between tether 50 aa and bridle lines 21 aa. A piece of string 33ar affixed to point 32 aa on the external of windbag 30 aa; or the rearof cover 536; pulled and secured to clip 533 by robotic limbs 522 mayserve the same purpose.

FIG. 6N illustrates sub-system 540; for coordinating the runningsequence of the multitude of windbags 30 aa. When a windbag 30 aa startsits power run from Station X to Station Y; the driven unit 55 ap may bemoved from point marked X (514 p′; 514 p″) to Y (514 p′; 514 p″) on theground. During the windbag retraction phase from Station Y to back toStation X; the driven unit 55 ar may be moved from point Y (514 p′; 514p″) to point X (514 r′; 514 r″); the driven unit 55 ar then waited forits turn before moving to point X (514 p′; 514 p″) to start its nextpower run again.

For ease of identification in FIG. 6A to 6N, apparatus related to powergenerating phase from Station X to Y had been assigned a letter “p”;while apparatus related to the return; retrieval; or retraction phasefrom Station Y to X had been assigned a letter “r”. For example: letter“p” in windbag 30 ap denotes a bag in “power run” phase. Letter “r” inwindbag 30 ar denotes a bag in “retraction” phase. Windbag 30 aa denotesreuse of a previously used number from the parent U.S. Pat. No.8,963,362.

Windbags 30 aa attached to guide-cables, wire-lines or guide-lines 304aa may be used for harnessing and extracting high altitude wind energy;said windbags running from one airborne workstation/or air-bridge toanother: e.g. Station X to Station Y. Work stations X and Y may beairlifted by means of a plurality of HAV-400 wind-cranes; and kept in arelatively stable location and position. Station X and Station Y may belocated at the same altitude. Or, Station X may be located at a heightof up to 2 km; while Station Y may be located at a height of up to 10km. Stations X and Y may be separated by a distance of up to 10 km.Windbags 30 ap released from upwind Station X may be driven diagonallyby the wind to downwind Station Y. Wind bags 30 ap attached to tetherlines 50 ap may be connected to ground/or surface based generators 55ag. The capture of the wind current by means of windbag 30 ap (driveunit 51); its power run from Station X to Y by the moving wind currentbeing used to power generator 55 ag (driven unit 55) to producerenewable electricity.

Spaced at regular intervals (distance of e.g. 100 m to 200 m apart)multiple wind bags 30 ap may be run on a single pair of guide-lines 304ap (Lane Ap) at the same time. At the SOR point, a deflated incomingwindbag 30 ar from EOR point may be checked, prepared, and put onstandby; ready to be deployed at the correct time. Wherein, said windbag30 aa may be refreshed by filling ring 22 ap; air-ribs 277 ap withcompressed air; via the air inlet port 531 of apparatus 530; andreleased through the gates 520 p; running from Station X to Station Yalong guide lines 304 ap′; 304 ap″; pulling tether 50 ap; poweringgenerator 55 ag. At Station Y windbag 30 ap may be depowered andcollapsed (air released from ring 22 aa; air-ribs 277 aa) via exhaustport 532 of apparatus 530. A piece of collapsible-extendablecylindrical/or, cone shaped plastic cover 536 tapered at one end may bepulled and slipped over the depowered windbag 30 ar to keep it in acollapsed position for the return journey. Retract line 33 ar located atpoint 32 aa pulled to point 31 aa and secured to clip 533 serves thesame purpose. Inlet port 25 ar ring 22 ar may also be clipped shut bymeans of robotic limbs 522. Or, embedded string 23 ar may be pulledtaunt to shut inlet port 25 ar. The bag may then be routed to returnguide-lines 304 ar′; 304 ar″; Lane Ar for retrieval by means of tether50 ar and retract motor 49 ag from Station Y to X.

FIG. 6O illustrates a parallel seaborne system 510 u; of the highaltitude airborne wind energy harvesting system 510 a as disclosed inFIG. 6A to FIG. 6N above with some variations. Such a parallel systemmay comprise of: a floating semi-submersible Station U 292 aa locatedupstream; an underwater submerged Station V located downstream on thesea bed 537; a floating semi-submersible Station W 292 aa located on thesurface above Station V. Water-bags 40 ap may be launched on powergenerating runs from surface Station U to submerged Station V located onthe sea bed 537. Enabled by means of guide-lines 304 ap′ and 304 ap″along run Lane Ap, Lane Bp, Lane Cp; etc. Sonar transmitter 299 saa maybe used to activate depowering of water-bags 40 ap at the EOR phase;working in tandem with sonar receiver 298 saa mounted at inlet port ring22 ap of bags 40 ap. Upon completion of the power run; the swivel rings308 ar′; 308 ar″ may be detached from guide lines 304 ap′; 304 ap″ bymeans of robotic hands 522 and attached to retract lines 304 ar; and thebags 40 aa moved to surface transition Station W located above StationV. This may be enabled by means of air pockets 538 formed in cavity 19ar; injected by robotic hand 522 held air nozzle 535. At Station W thebridle lines 21 aa and bag 40 aa may be detached from line 50 aa. Line50 aa are retracted to Station U at speed. The water-bags are stackedtogether, then retracted from Station W back to Station U by means ofsurface vessels 539 bearing stacks of water-bags 541 via pulley system48 aa powered by HAV-400 wind crane. The bags are recycled and reusedrepeatedly.

Station V and Station W may be connected by a sub-system 540 for raisingthe submerged Station V from the seabed 537 to the surface level forservicing and repair works at intervals. And for lowering andreinstalling back Station V into its original location and position tocontinue working. System 540 may include motorized winches 59 ap (port);59 as (starboard); loops of dual winching lines 542 p′; 542 p″; and 542s′; 542 s″; seabed mounted pulley wheels 48 ap (port); 48 as(starboard); ballast tanks 543 (varying the amount of air to watercontent provides variable buoyancy); airbags 544; mounting pillars 545piled into the seabed 537. Station V may be securely anchored to twinpillars 545 by means of designated slots, clamps, attachments, etc. Dualpairs of winch lines 542 p′; 542 p″ and 542 s′; 542 s″ may be used toconnect Station V and Station W. At Station W winch lines 542 p′; 542 p″and 542 s′; 542 s″ forms a loop around port winch 59 ap and starboardwinch 59 as. The winch lines extends to two pulley wheels 48 ap and 48as affixed to the seabed 537; forming two complete loops. Line 542 p′and 542 s′ extending from Station W may be securely affixed to the sidesof Station V at points 546 p and 546 s; and continues on, loopingthrough the pulley wheels 48 ap and 48 as until the lines portions (nowindicated as) 542 p″; 542 s″ reached winches 59 ap; 59 as.

Such a configuration enables Station V to be brought up to the surfacefor repair works. Ballast tanks 543 normally full of water may be filledup with air displacing the water; creating buoyancy for lifting StationV. Airbags 544 located between the seabed 537 and the bottom of StationV may also be filled up with air to create added buoyancy. Reducing theweight of Station V; such that winches 59 ap and 59 as may lift it up tothe surface with ease. Ballast-tanks 543 and airbags 544 may be inflatedby means of compressed air from storage cylinders 203 aa via air lines204 aa; or by means of air lines 204 aa connected to surface based aircylinders 203 aa or a compressor located at Station W. This may beenabled by means of underwater drones 230 aa equipped with robotic limbs522.

Seaborne eco-system 300 aa may comprise of: power generation stations U;V; W; mooring buoys 508; FPSO vessel 511 with hydrogen generation plants509; atmospheric carbon-dioxide (CO2) capture plant 547; diesel ormethanol production plants 548 for manufacturing carbon neutral liquidfuels; tankers 296 taa with spherical tanks 549 for offloading hydrogenvia transfer line 551. CO2 derived from carbon capture and sequestration(CCS) projects may also be brought in by CO2 tankers to providefeedstock for liquid fuel production plants 548. Tankers 296 taa andother ocean faring vessels may be powered by means of glider-dronesHAV-400; or its variant HAV-400M. Anchoring lines 295 aa from themooring buoys; semi-submerged columns 552 and submerged pontoons 553 ofStation U; Station W; may be anchored by means of pillars 545 piled intothe seabed 537; or by means of suction cups 550 attached to the surfaceor floor of the seabed 537. Station V may be affixed to piles andpillars 545 extending from the seabed 537. Or, a subsea based Station Vsuspended in the sea below Station W may be anchored to the seabed pilesusing lines 295 aa. Spar mounted facilities may also be adapted for usewhere applicable.

The height of the stations (Station U; Station W) above the sea surfacemay be controlled by the flooding or de-ballasting of the ballast tanksinside the columns 552 (legs) and bottom pontoons 553 of thesemi-submersible stations. Flooding of ballast tanks reduces itsbuoyancy; and the station sink deeper/lower. De-ballasting of ballasttanks increases its buoyancy; the station rises higher up. Suchflexibilities may be used during maintenance of Station V. Station W maybe lowered down near to the sea surface; then Station V may be raised upto the surface by means of winch lines 542 p and 542 s; buoyancy tanks543 and lifting air bags 544. Heavy duty chains may be used to link andattach the two stations together; one on top of the other. Station W maythen be raised to a higher level by increasing the buoyancy of itsballast tanks. Thus enabling repair works to be carried out on Station Vunder dry dock conditions.

All phases of execution may be automated by means of an integratedsystem comprising: computerized smart artificial intelligence (AI);robotics; cameras; sensors; actuators; activation mechanisms;radio-frequency transmission; sonar transmission; remote sensing commandand control systems.

FIG. 6P illustrates a variant reconfigured airborne windbags system 76av; with improvements in productivity, efficiency; fuel savings;zero-carbon-pollution wherein a zero-emission vehicle (ZEV) comprisingHAV-400 (drone navigation unit) spearheaded a multitude of windbags 30ap in a power generating run; as compared to prior art system 76 (referFIG. 5A of U.S. Pat. No. 8,963,362). HAV-400 replaces UAV-80 as dronenavigation unit. FIG. 6Q illustrates the retraction phase of system 76ay. The navigation unit may consist of aerial drones comprising: gliderdrones; remote controlled drones; autonomous drones; or any type ofsuitable drones. Said drone navigation unit HAV-400 provides a means ofdirectional control; guidance; powered flight if required to return tobase. HAV-400 may be outfitted with winch 59 aa; with the winch line 33ap affixed to point 229 ap on tether line 50 ap. The retract line 33 aamay be reconfigured to connect winch 59 ap (mounted inside HAV-400) viapoint 227 ap (on the outside of HAV-400's body) to point 229 ar ontether line 50 aa. Compressed air generated by the ram-air-turbine 71 aaof HAV-400 may be used to inflate ring 22 ap and air ribs 277 ap bymeans of an air-line 278 aa integrated with tether 50 ap. During the endof run (EOR) phase, gearbox 53 ag of driven unit 55 ag may be put onfree gear; wherein said windbag 30 aa flows freely with the wind currentexerting zero tensile force on tether 50 aa. HAV-400 may use winch 59 apto wind back the retract line 33 ap until point 229 ap coincides withpoint 227 ap on body of HAV-400. Optionally, it may turn on itspropulsion system to fly a short distance to point 229 ap. A radiofrequency transmitter (RF) 299 raa may be installed at point 229 aa. Aradio frequency receiver cum RF signal homing device 554 r may beinstalled at point 227 ap. In case of retract line 33 ar failure; aradio-frequency transmitter 299 raa positioned at joint 229 ar; and aradio-frequency receiver cum homing device 554 r installed in the bodyof HAV-400 at point 227 ar may be used. Homing in on the RF homingsignal coming from point 229 ar; HAV-400 flew towards 299 raa untilpoints 227 ar and 229 ar coincides; and latches itself securely ontoline 50 ar near to point 229 ar by means of specially configured andcustomized attachments comprising: hooks; rings; clips; grippers, etc.Wherein said multiple windbags 30 aa; 30 ab; 30 ac reversing directionbehind HAV-400; are instantly depowered. As their aft joining point 32ap faces fore, into the oncoming wind (W); while the fore bridle linesjoining point 31 ap faces aft; as illustrated in FIG. 6Q. Theglider-drone HAV-400 and line of depowered bags may then be retractedback to the start-of-run (SOR) point 16 aa by means of electric poweredretract motor 49 aa which reeled back tether line 50 ap. Such anarrangement eliminates the need for a long retract line 33 aa all theway from the SOR point 16 aa to the EOR point 288 aa. And requires onlya short portion of retract line 33 ap from point 229 ap to point 227 ap(and winch 59 aa) to be used. The inlet-outlet port 227 ap on theexternal body of HAV-400 allows retract line 33 ap to pass through tointernal winch 59 ap. This modification totally eliminates the need forHAV-400 to fly all the way from EOR point 288 aa back to SOR point 16 aaunder its own power. Thus saving fuel; eliminates carbon pollution;improving productivity and efficiency of the improved system 76 ay.

A variant reconfigured parallel underwater system 222 av using dronenavigation unit UUV-230 aa/or HAV-200 aa may be used as a substitute forsystem 222 (refer FIG. 5A; U.S. Pat. No. 8,963,362); or to improve it.The reconfigured system 222 av may comprise of a modifiedzero-emission-vehicle (ZEV) UUV-230 av equipped with pneumatic/orbattery powered winch 59 aa; air tanks 203 aa; air lines 204 aa; 278 apcombined with tether line 50 ap; etc. The retract line 33 ap may bereconfigured and/or modified to connect winch 59 ap (mounted insideUUV-230 av) via point 227 ap (inlet and outlet port) to point 229 ap ontether line 50 ap. A sonar transmitter 299 saa may be installed at point229 ap. A sonar receiver cum sonar signal homing device 554 s may beinstalled at point 227 ap. In case of retract line 33 ar failure; asonar transmitter 299 saa positioned at joint 229 ar; and a sonarreceiver cum homing device 554 s installed in the body of UUV-230 aa atpoint 227 ar may be used. Homing in on the sonar homing signal comingfrom point 229 ar; UUV-230 aa propels itself towards 299 saa untilpoints 227 ar and 229 ar coincides; and latches itself securely ontoline 50 ar near to point 227 ar by means of specially configured andcustomized attachments comprising: hooks; rings; clips; grippers, etc.Hydrogen fuel cells (using hydrogen gas generated by eco-system 300 aa)and batteries may be used to provide electric propulsion for said ZEVdrones; HAV-100 aa; HUV-200 aa; UUV-230 av; HAV-400. Renewable fuels mixcomprising methanol; biodiesel, etc. may also be used. Bottledcompressed air from cylinders 203 aa may be used to inflate inlet portring 22 ap and air ribs 277 ap by means of air-line 278 aa integratedwith tether 50 ap. Two-way communications between the Control Center(command; execution signals) and the drone navigation unit (feedback;status signals) may also be enabled by means of a hard wirecommunication line integrated with the tether line 50 ap.

FIG. 6R illustrates the use of naturally occurring reliefs andgeological features on the seabed or the sea-floor 537 as anchoringpoints for securing lines 295 aa to anchor mooring buoys 508;semi-submersible production stations U, W, 292 aa; floating flat-bedplatforms 293 aa; inflatable floating bodies 294 aa; and othercomponents of ecosystem 300 aa. Such geologic features may compriseseamounts 555 and islands 560. Submerged seamounts 555 may comprise:guyots 556; pinnacles 557; knolls 558; etc. Such that surface unevennessin the topography comprising: holes; indentations; protrusions;fissures; cracks; nooks and crannies, etc. of the seamounts 555;submarine ridges 559; trenches 561; canyons; seafloor 537, etc. may beadapted, modified and converted for use as anchoring points for securinglines 295 aa. By means of man-made apparatus comprising: piles 562 andpillars 546; reinforced concrete beams 563; cement plugs 564 inserted orbuilt into artificial and/or natural caverns 565; holes 566 drilled andartificial grooves 567 cut into suitable places of the rocky features ofthe seamounts 555 and islands 560, etc. Such that anchor lines 295 aamay be secured to pillars 545 and piles 562; lines looped around smallhills, pinnacles 557 ridges 559; lines looped through holes 566 heldsecurely in recessed grooves 567; etc.

FIG. 6S illustrates an enlarged view of a strategically locatedreinforced concrete beam 563 placed in position in between the V-shapedvalley formed by two seamounts; a guyot 556 and a ridge 559 with thesecuring line 295 aa exiting from the opposite side of the V-shapedvalley; for securing a floating body on the surface in position. Pillarand beam 563 may be locked in position by means of U-shaped piles 568inserted into the seabed 537. Also illustrated is an enlarged view of areinforced concrete wedge 564 built inside a small natural or artificialcavern 565 with a narrow opening; with line 295 aa attached to theexposed tip of the conical/or pyramidal shaped cement plug 564. All suchmodifications and adaptations shall be carried out with the leastdisruption to the existing natural ecosystem.

FIG. 6T to FIG. 6X illustrates system 570 for channeling sea watercurrent by means of man-made sea walls 571 p (port) and 571 s(starboard); said walls 571 may be configured into a V-shaped apparatus.An inclined overhead ceiling 571 c may be used to divert water flow fromabove. Seafloor 537 f (floor) forms the bottom floor. A skid 572 ofturbines 471 may be located at the V-shaped apex 569 where convergingwater flowed fastest due to constriction caused by the walls of theapparatus 570. A large inlet port converging the water to flow through asmall constricted outlet or port. Wherein said skid 572 comprising amultitude of water turbines 471 may be used to harvest the kineticenergy of the high speed water current efficiently. Optionally, saidapex 596 may be configured as a tunnel-like structure 569 t; into whicha specially configured seaborne hydro-electric generation tunnel 575carrying a plurality of large turbines 471 units may be slotted/orinserted.

FIG. 6T illustrates the plan view of a funnel shaped configuration ofsea walls 571; while FIG. 6U illustrates the perspective view. Waterintake port 573 of apparatus 570 may be protected by a cage and mesh 573c which acts as a filter keeping out marine wildlife. FIG. 6Villustrates the front view of an individual turbine 500 b mounted in asquare shaped frame 574. FIG. 6W illustrates the perspective view of askid 572 of turbines 471. This structural configuration enables aplurality of turbines 471; 500 b; etc. to be slotted into and stacked upin the skid 572. One unit on top of another. Wherein, rows upon rows;stacks upon stacks of turbines may be arranged inside said skid 572.Apparatus 570 and skid 572 may be anchored to the sea floor by means ofpillars 545 or piles 562. The whole skid 572 may be installed/or removedby means of winches 59 as; 59 ap; mounted on semi-submersible Station W292 aa; or by means of floating crane barges for periodic maintenance.

FIG. 6X illustrates a variant configuration wherein said apex 569 may beconfigured as a tunnel-like structure 569 t; with a flip-able top roofcover. Such that this top roof cover may be flipped open or close; andsecured in place. A specially configured seaborne hydro-electricgeneration tunnel 575 containing a plurality of large water turbines471; or 500 b; etc. may be slotted into/or removed from the flip-abletop roof cover of tunnel 569 t. Such that apparatus 575 may be loweredinto tunnel 569 t during installation; or lifted out by means ofsemi-submersible Station W 292 aa; or crane barges for maintenance. Acentral shaft 576 for mounting said plurality of turbines may beconfigured in the center supported by peripheral beam 575 s. Shaft 576may be split into sections 576 a; 576 b; 576 c; and configured forseparate operation of each individual turbine units. The rotationalmovement of the turbine unit 471 a may be transmitted from theindividual horizontal shaft section (e.g. 576 a) to an angulartransmission gear box 476 u; to vertical shaft 475 u; to generator unit577 a. Submarine cable 457 u may be used for transmission of powergenerated to shore or surface vessels 511.

FIG. 6Y illustrates system 580; a plurality of water turbines suspendedin the sea. A mooring buoy 508; or, a floatation-ballast tank 578 on thesea surface enables line 457 u to hold the submerged turbines 471; 500a; 500 b; in place while the other end of line 457 u may be anchored tothe sea floor by means of a suction cup device 550; or to other meanssuch as piles 562. Top surface of tank 578 may incorporate solar cells579 for generation of electricity to power navigation lights and RFsignals. The body of turbines 471; 500 a; 500 b; may be outfitted withswim control surfaces comprising: fins, planes 205 aa; 207 aa;stabilizers 208 to keep them in proper orientation. Optionally, thewhole apparatus comprising: the ballast tank 578 and line of turbinesmay be configured to be totally submerged below the sea surface. Inorder to avoid hazards posed by surface ships. This may be effected bymeans of: air tanks 203 aa; air-lines 204 aa; and an automated systemfor buoyancy control of ballast tank 578.

All critical components of the above water-turbines; their electricalgeneration and transmission systems, etc. may be enwrapped in animpervious layer of cover/or protective materials. Such materials maycomprise plastics; polymers; fiber-glass; carbon composites;poly-ethylene; poly-propylene; etc. Such protective materials forinsulation of electrical components and corrosion prevention may besprayed-on, applied as a coating, wrapping, embedded, impregnated, etc.

Normally renewable energy generation may be associated with adistributed network for direct extraction and generation of electricalpower. However, in a variant configuration renewable energies extractedby a multitude of drive units 51 aa may also be congregated intointegrated driven unit 585 a; 585 b; 585 c; comprising a centralizedgeneration plant 585 for production of electricity as illustrated fromFIG. 7A to FIG. 7H.

FIG. 7A to FIG. 7H illustrates system 600 comprising: (a) A DistributedSystem for Extraction of Energies from high altitude wind currents anddeep sea ocean currents by means of drive units 51 aa; (b) a tensileforce transmission system for channeling and transmitting this extractedenergies to a; (c) utility scale Centralized Power Generation Plant 585.Said generation plant 585 comprises: driven unit 584 a; 584 b; 584 c;line reel drums 582; gearboxes 583; clutch boxes 587; retract motors589; for producing renewable electricity; wherein, variant driven unitsmay include counter-rotational generators 590 d; 590 h. The energiestransmitted may be converted into other forms of energy; or for doingother useful work.

FIG. 7A illustrates a single drive unit 51 aa comprising of: a pluralityof drones HAV-400 s linked in series flying one on top of another;connected by a single tether 50 aa to generator 55 ag. Combined use ofsuch a multitude of airborne glider-drone HAV-400 wind-cranes produces amuch more powerful lifting force to power generator 55 ag; than a singleunit. Such a configuration may also be used to power the systems ofcentralized power generation plant 585.

FIG. 7B illustrates system 600 comprising of: a centralized powergeneration plant 585 connected to and powered by a multitude of highaltitude wind energy extraction apparatus made up of drive units 51 aacomprising: HAV-100 aa; windbags 30 aa; HAV-400; windbags system 76 av;morphing kite-glider-drone vehicles HAV-400M armed with windbags andwing-suits 30 aa. The generation plant 585 may comprise of a pluralityof driven units 585 a; 585 b; 585 c connected to a single common shaft581. Wherein, said driven units 585 a; 585 b; 585 c may be powered by aplurality of drive units: 51 aa; 51 ab; 51 ac; etc. The common shaft 581linked together all components of the plurality of driven units 585 a;585 b; 585 c. Wherein, an individual driven unit 585 a may comprise:line reel drum 582, gearbox 583, generator module 584 a; bearing boxes586; clutch box 587; retract motor 589. Said plurality of driven units585 a; 585 b; 585 c may be configured to move in unison with each otherin a single direction of rotation (stators-rotors configuration); justlike conventional generators the world over.

A variant configuration allows and enables each individual driven unit(e.g. 585 a; 585 b; 585 c) to move in different directions of rotation.Wherein, said main shaft 581 may be adapted into individual section 581a; 581 b; 581 c; etc. Such that each said section 581 a; 581 b; 581 c;may be connected together; or segregated from each other by means of anapparatus 587. Working like a simplified vehicle's clutch-gear system;apparatus 587 may be used to link and connect two shaft sections (e.g.581 a; 581 b) together when it is shifted into an engaged position. Whenit is shifted into the neutral position (freed), apparatus 587disengages this linkage; breaking the connection between the twosections (e.g. 581 a; 581 b); allowing them to rotate freely and turnindependently of each other. Apparatus 587 may be also be integratedwith gearbox 583 into a single unit; such that a particular drive unitmay be engaged; or disengaged as and when required (refer FIG. 7C). Suchflexibility enables the use of counter-revolving generators comprising590 d; 590 h. For example: driven unit 585 a; driven unit 585 c mountedin section of shaft 581 a; 581 c may be configured to rotate clockwise;whereas driven unit 585 b mounted in section of shaft 581 b may beconfigured to rotate anti-clockwise. Such that said opposing directionsof rotations may be used to power variant generator modules such as: 590d; 590 h; configured with dual counter-rotating rotors comprising: rotorwire coils and rotor magnets.

FIG. 7C illustrates details of FIG. 7B wherein the line reel unit 582;gearbox unit 583 and clutch unit 587 may be integrated together as asingle unit; powering the generator 584 by means of main shaft 581. Thecombined unit 585 may be assigned new identifying numbers: line reeldrum (582); gear box (583); retract motor (589). Retract motors 49 agmay be directly connected to the line reel drums 582 (bypassing thecommon shaft 581) and identified as 589.

FIG. 7D illustrates system 600; a variant driven unit 585 d configuredwith a variant vertically disposed twin rotating discs generation unit590 d′; 590 d″; 590 d′″. FIG. 7E illustrates details of FIG. 7D. Drivenby a plurality of drive units 51 aa via shaft 581; said double discscomprising: rotor coiled wire disc 486; rotor magnet disc 487; turningin opposite directions; counter rotates against each other to generateelectricity (refer FIG. 4E; FIG. 4F). Generator 590 d of FIG. 7E may beused in the centralized power plant 585 to generate electricity.Wherein, said individual driven units 585 d′; 585 d″; 585 d′″;associated with individual sections of shaft 581′; 581″; 581′″; may beconnected to and powered by a multitude of: (a) high altitude flyingwind energy extraction apparatus made up of drive units 51 aacomprising: HAV-100 aa; 30 aa; HAV-400; HAV-400M; windbags 30 aa system76 av; and (b) deep-sea diving water energy extraction apparatus made upof drive units 51 aa comprising: HUV-200 aa; water-bags 210 aa;water-bags 40 aa system 222 ay. The drive units 51 aa may be linked tothe driven units 585 d′; 585 d″; 585 d′″; by means of: (a) pulley wheels48 aa; (b) line reel drums 582; (c) dual line reel drums 582 cum 588with transmission lines 591 protected by hard cover 592. This system ofusing auxiliary apparatus enables drive units 51 aa to be distributed atan extended range/or a long distance away from the centralizedgeneration plant 585. Providing an extended range and an enlargedarea/or volume for extraction of airborne and waterborne energies.

FIG. 7F illustrates a variant line reel spool 582 in which dual units ofline reel drums 582; 588; may be joined together with a shaft 593; andbearing boxes 586 mounted on a supporting body frame 594. Line reel drum582 may be loaded with tether lines 50 aa. While line reel drum 588 maybe purposely kept empty; and linked to line reel drum 582′ (full drum).Such that when the lines are transferred from drum 582′ to drum 588;drum 588 may be fully loaded with transmission lines 591 from drum 582′(refer FIG. 7D, drive unit 222 av). Such auxiliary apparatus may be usedas a transfer mechanism for intermediate energy transmission between thedrive units 51 aa and driven unit 581 a; when the two units may beseparated by a long distance, e.g. 3-5 km apart.

FIG. 7G illustrates system 600; a variant driven unit 585 h configuredwith a variant horizontally disposed twin rotors generation unit 590 h.FIG. 7G also illustrates the combined use of auxiliary apparatus (a) to(c) disclosed in FIG. 7D above; together with: (d) extended transmissionshafts 595; (e) and a variant angular transmission gear box 583 v; etc.in the extraction of wind and water energies from an enlarged area/orvolume of the natural ecosystem. Such apparatus may be used to overcomephysical obstructions caused by hills, cliffs, corners, sharp bends,etc. and improve operational flexibility and dexterity. The extendedtransmission shafts 595; and tensile force (energy) transmission lines591 running in between line-reel-drums (LR1) 582′; (LR2) 582″; (LR3)582′″ and the gear boxes 583; 583 v; may be covered by conduit pipe 592for safety purposes.

The following description on the port side of generator 590 h; mainshaft 581 p; illustrates combined use of the plurality ofline-reel-drums: 582′; 582″; 582′″; powered by HAV-400. For simplicitythe drums may be referred to as: LR1; LR2; LR3. The LR1 comprises ofnormal line reel drum 582′ fully loaded with tether line 50 aa. LR2;LR3; and lines 591 in between them may comprise the tensile forcetransmission system. To start with, LR1 may be loaded full of line 50aa. LR2 may be empty; LR3 may be loaded full of lines 591. Operation ofsaid plurality of line-reel-drums: 582′; 582″; 582′″; for transmissionof tensile force produced by HAV-400 on tether line 50 aa to generator590 h may be described in the following steps: Tensile force on tetherline 50 aa may be transmitted by means of pulley wheels 48 aa′ and 48aa″; causing LR1 to rotate. This rotational movement is transmitted fromLR1 to LR2 by means of extended transmission shaft 595′. This causesempty LR2 to wind in lines 591 from the fully loaded LR3; causing LR3 torotate. LR3 then transmitted this tensile force by means of extendedtransmission shaft 595″ to gearbox 583 p; which transmitted this tensileforce to the port side main shaft 581 p; causing it to rotate. Thisshaft rotation is transmitted to generator 590 h; causing the rotor wirecoil 474 to rotate.

The following description illustrates use of a plurality of extendedtransmission shafts 595; gearboxes 583 and a variant angulartransmission gearbox 583 v; for transmitting the tensile force producedby HUV-200 aa to generator 590 h (port side; shaft 581 p). Tensile forcegenerated by HUV-200 may be transmitted by means of: the tether line 50aa to line reel drum 582 via pulley system 48 aa; causing drum 582 torotate. This rotational movement may be transmitted by means of extendedtransmission shaft 595 a to variant gearbox 583 v; then to gearbox 583p″ by means of extended transmission shaft 595 b; then to gearbox 583 p′mounted on main shaft 581 p by means of extended transmission shaft 595c. Gearbox 583 p′ then transmitted this torque to shaft 581 p; which isthen transmitted to generator 590 h; causing the rotor wire coil 474 torotate.

Drive units HAV-400 and HUV-200 aa may take turn to run. When one driveunit is working; the other may be retracted and put on stand-by.Similarly, drive units HAV-100 aa and HAV-400 located on the starboardside of generator 590 h; main shaft 581 s; takes turn to operate topower generator 590 h; causing rotor magnet 476 to rotate. Thecounter-rotation of said rotor wire coil 474 and rotor magnet 476enables utility scale generator 590 h; and thus the Centralized PowerGeneration Plant 585 to produce renewable electricity. Instead of twoalternate drive units on each of the port and starboard side ofgenerator 590 h; multiple units may be configured and sequenced to runproviding much more powerful torque for 590 h.

Such a tensile force transmission system comprising: energy transmissiontools, equipment and apparatus provides an enabling means for operationof system 600. A system for harvesting energies from the naturalenvironment by means of a multitude of distributed apparatus; and thetransmission of this collected energies; to a central power plant 585for generation of renewable electricity.

FIG. 7H illustrates details of FIG. 7G. Driven by a plurality of driveunits 51 aa via shaft 581 p; 581 s; said double rotors generatorcomprising: rotor wire coil 474; rotor magnet 476; may be configured toturn in opposite directions; counter rotating against each other togenerate electricity (refer FIG. 4C; FIG. 4G). If the wire coil 474rotates clockwise; then the magnet 476 rotates anti-clockwise. Or,vice-versa. Both of the rotors comprising: wire coil 474 and magnet 476may be individually connected to the shaft 581 p (port side); 581 s(starboard side) and powered by its own dedicated drive units. Port sidedrive units 200 aa and 400 may be connected directly to the shellmounted wire coil 474 by means of shaft 581 p and yoke 484 p. Wire coil474 may be supported on the starboard side by yoke 484 s and bearingring 596. While the starboard side drive units 100 aa and 400 may beconnected directly to the center mounted electro-magnet 476 by means ofstarboard side shaft 581 s. Generator 590 h may comprise of rotor wirecoil 474; rotor magnet 476 linked by individual sections of shaft 581 p;581 s; wherein, said sections 581 p; 581 s may be held in position bymeans of a bearings 597 sleeve 598. Such that even though sections ofshaft 581 p; 581 s may rotate in opposing directions; they may bealigned with each other. The sections 581 p; 581 s; may be supported bya plurality of bearing boxes 586 affixed to pedestals 599. Generator 590h may be protected by external body cover 473; and mounted on a solidbase 594. Compared to conventional rotor-stator generators, such acounter-rotating configuration of system 590 h enables much higherefficiency and productivity. As the speed and movement of the generatingsurfaces of both rotating elements relative to each other may bedoubled. A variable electrical (or magnetic flux) controller 466 may beused to vary the supply of current to the electro-magnet 476 of thegenerator; and thus vary the production of electricity relative to thewind power available at the point in time.

Conventional combined cycle power systems typically have a primary driveunit to power a stator-rotor generator; then use the exhaust flue gas;(or recover the heat energy by generating steam) for powering asecondary drive unit cum generator.

FIG. 7I illustrates a variant combined cycle power generation plantusing a counter-rotating generator 590 h. Input to the primary driveunit 601 comprising fuel; high pressure steam; etc. may be routed bymeans of pipe 602. Wherein, the exhaust flue gas; or steam from primarydrive unit 601 located on the starboard side of said generator 590 h;may be routed via pipe 603 to the secondary drive unit 604 (located onthe port side) to drive said generator 590 h. Such that the primarydrive unit 601 drove the rotor magnet 476; while the secondary driveunit 604 drove the rotor wire coil 474. After drive unit 604; theexhaust may then be routed via pipe 605 to the tertiary drive unit 606for driving a steam turbine-generator; or flue gas turbine-generator toproduce power. Or a waste heat generator to produce low pressure steamor hot water.

FIG. 8A illustrates a variant submerged system 570 u of FIG. 6T to FIG.6X; wherein a reconfigured water-bag 40 aa may be integrated with aseaborne hydro-electric power generating tunnel 575 v for producingrenewable energy. Tunnel 575 v may be similar in purpose to the penstockof a HEP dam. Water-bag 40 aa may be used as a funnel to entrap the flowof sea water; concentrate this large flow of water into a constrictedtunnel 575 v fitted with a plurality of turbines 471 to generateelectricity. Turgid inlet port ring 22 aa and water-ribs 277 aa keptwater-bag 40 aa in functional shape. The light-weight tunnel 575 v madeof fiberglass; carbon fiber; Kevlar, plastics, etc. may be and attachedto a semi-submersible Spar buoy 607 on the water surface. The bottomportions of the submerged water-bag 40 aa and the power generatingtunnel 575 v may be securely anchored by means of a plurality of lines295 aa to the seabed 537; seamounts 555 comprising: ridges 559; beams562; plugs 564 inserted into cavern 565; holes 566 with grooves 567. Thewhile the upper portions may be anchored to floating buoys 508 on thesea surface and/or submerged ballast tanks 579 by means of lines 457 u.Fishing nets 573 c may be used to keep out marine wildlife. Electricitygenerated by the seaborne hydro-electric power generating system 570 umay be routed by means of cable lines 457 to ground stations onshore/or, to mooring buoy 508; FPSO 511 equipped with electrolyzerplants 509; ecosystem 300.

FIG. 8B illustrates a parallel airborne system 570 a. Such a system mayalso be configured and used for airborne deployment of windbags 30 aa.Wherein, similar to the underwater system 570 u; said airborne systemmay comprise of a plurality of glider-drones HAV-400; HAV-400Mwind-cranes carrying aloft a large windbag 30 aa connected to alight-weight tunnel 575 bearing a plurality of turbines; by means of aplurality of tether lines 50 aa and mooring lines 46 aa. Inflated inletport ring 22 aa and air-ribs 277 aa kept windbag 30 aa in functionalshape. The upper portions of the windbag 30 aa and tunnel 575 a may belifted up by means of a plurality of tether lines 50 aa; bridle lines 21aa attached to a plurality of HAV-400 s; balloons filled with LTA gases;etc. While the bottom portions may be anchored to a plurality of boats220 aa; mooring buoys 508; semi-submersible Spar buoy 607 on the seasurface. On land the system may be secured to the ground; adapted hills;mountains and valleys by means of a plurality of tether-cable 478 andpiles specially inserted for mooring the system. Electricity generatedby the airborne aero-electric power generating system 570 a may berouted by means of tether-cable 478 to ground stations/or to mooringbuoy 508; FPSO 511 equipped with electrolyzer plants 509; a combinedecosystem 500 and 300.

FIG. 8C illustrates a system wherein, a plurality comprising pieces orstrips of fabric materials 415 b may be carried aloft by means of aplurality of light duty glider-drones HAV-400; or HAV-400M wind cranes.A variant system of power kites gliders 400 v; /or kite drones 400 vwhich use only wind energy to generate aerodynamic lift; tether 50 aaand mooring lines 46 aa; may also be used. Said strips of light-weightmaterials may comprise solar fabrics 415 b for harnessing solar energyto generate renewable electricity. Such materials may be mounted on alayer of aero-foams 608; light weight foams filled with bubbles/orpockets of lighter-than-air gases: comprising helium; hydrogen; etc.Such that said pieces of aero-foams 608 may be buoyant to a certaindegree due to the presence of LTA gases used in its manufacture;light-weight; and maintains its physical shape. Multiple strips of suchaero-foams bearing solar fabrics 415 b may be joined together by meansof lines 609 forming an airborne flying carpet for harnessing solarenergy. A plurality of lines 609 may also be used by a plurality ofHAV-400 to lift the apparatus up. Gaps of empty space left in betweensaid strips of interlinked aero-foams 608 cum solar fabrics 415 b allowspassage of wind current. Power generated may be channeled by means ofcable-tether 478. Such light weight aero-foams 608 and solar fabrics 415b may also be used on water surfaces as floating solar energy collectorsas illustrated in FIG. 8D.

Whenever and wherever practicable all activities, equipment, vessels,etc. of present invention shall be powered by means of zero-carbonenergies generated by the bagged power generation system. All activitieswould be carried out in compliance with relevant government regulations;international protocol; IPCC requirements; in consultation with NGOs;environment groups, etc. expediting change-over of our presentcarbonaceous; hydrocarbon based economy to a clean hydrogen-electrifiedeconomy powered by renewable energies.

Global climate change is a man-made catastrophe. Therefore, thisexistential threat may be aggravated or mitigated dependent upon: humandecisions; actions and reactions. CO2 caused climate change is badenough. The main danger lies in the hijack of climate change by methanegas emissions—from the deep-sea methane hydrate deposits; Arctic andAntarctic methane hydrate deposits; stored underground for millions ofyears. When CO2 induced global warming heated up these stored depositsof carbon; causing their inadvertent release into the atmosphere. Thatmay well be the start of human extinction. What? Mankind—to follow thedinosaurs into extinction; history? And this is (may) already (be)happening! Because methane gas is 100 times more potent than CO2 in itsfirst ten year period. It is 20 times more potent over a 100 yearsperiod. Another gas that accompanies methane release in smallerquantities, nitrous oxide N2O is 300 times more potent than CO2. Humansmust use our own personal knowledge; common sense; judgment; moral andreligious values; in our search for answers to questions in which we maynot be experts. Scientific papers; peer reviewed documents; climatedata; Paris Climate Accord; etc. may provide more information. Internetsearches may include phenomena such as: “methane bubbles in Arcticlakes”; “methane blow holes”; “exploding pingo”; “trembling tundra”;“7000 under-ground methane gas bubbles poised to explode in the Arctic”;methane gas bubbles trapped in ice in Alaska, tundra; Arcticexpeditions; surveys of Centre for Arctic Gas Hydrates and Environment(CAGE); “SWERUS”; undersea methane flares; etc.

Mission-Vision Statement: To reduce; eliminate Global Warming; to saveour spaceship—Planet Earth from the dangerous effects of Global ClimateChange! The use of drones to serve humanity! To produce clean energy; topreserve clean air and clean water for all of us! We must alwaysremember this; that we only have:

One race—Humanity! One planet—Earth! One common Destiny!

We must all work hard to preserve; not destroy, our one and only “livesupport system”—Earth's biosphere! For in the fate of mother Earth; andin our own hands, lies our common destiny—for all things living on thisplanet; and future generations of—plants; animals; humans. It is ourcommon duty and responsibility to do our part: innovators,entrepreneurs, financers, governments and NGOs, etc. To Save The World,Our World! “Look high, look far. Our aim the sky, our goal the stars!”To an inventor the sky's the limit.

While the preferred embodiments of the devices and methods have beendescribed in reference to the environment in which they were developed,they are merely illustrative of the principles of the inventions. Theelements of the various embodiments may be incorporated into each of theother species to obtain the benefits of those elements in combinationwith such other species, and the various beneficial features may beemployed in embodiments alone or in combination with each other. Otherembodiments and configurations may be devised without departing from thespirit of the inventions and the scope of the appended claims.

I claim:
 1. A system for generation of electrical power comprising: anaerial drone having an inner frame covered by an external airframehaving layers of airbags stacked on top of each other, the aerial dronehas at least one tether line attached to the aerial drone; a driven unithaving a body that includes a generator, the driven unit attached to theaerial drone by the at least one tether line; and a computer incommunication with the aerial drone and configured to control theinflation and deflation of the airbags of the aerial drone; whereincomputerized sequential manipulation of the plurality of said airbag'sinflation and deflation controls the aerial drone's external shape andcontours and enables generation of electrical power from captured windcurrents so that the driven unit 500 a is lofted by the aerial drone;and wherein inflation of the airbags creates kinetic energy that iscaptured within the air bag and transmitted to the driven unit generatorto generate electrical power.
 2. The system of claim 1 wherein theaerial drone further comprises at least one air turbine contained withinthe inner frame of the aerial drone that provides compressed air to theaerial drone for inflating the airframe of the aerial drone.
 3. Thesystem of claim 2 further comprising an airbag sub-system including agas control and distribution system for controlled release of compressedgas to selectively inflate and deflate airbags.
 4. The system of claim 3further comprising a gas recycling system for recycling the compressedgas from deflated airbags of the aerial drone.